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 method for stationing a satellite comprises a transfer phase, during which the satellite moves on an elliptical geosynchronous orbit, the orbit being deformed progressively by application of a thrust by electrical or hybrid electrical-chemical propulsion to bring it closer to a geostationary orbit. The transfer step comprises a substep during which, during a plurality of revolutions of the satellite, the thrust is stopped for a fraction of orbital period and tests of a telecommunications payload of the satellite are performed in the absence of thrust.

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.

When a deorbiting satellite, which is one of artificial satellites belonging to a first satellite constellation, deorbits and drops from an orbit of a first orbital altitude zone, a second satellite constellation widens a relative angle of any adjacent two orbital planes of a plurality of orbital planes and thereby allocates a free orbit area in a second orbital altitude zone. The deorbiting satellite passes through the free orbit area of the second orbital altitude zone.

A vehicle and method enabling propulsive flight from the Earth's surface to and from the Moon's surface returning to horizontal Earth landing along an airstrip. This reusable geolunar shuttle vehicle can employ external drop tanks, and function as the final propulsive stage of a multi-stage vehicle which can be: 1) expendable, reusable or party reusable; 2) ground-launched, sea-launched, or air-launched; 3) single-launched or multiple-launched with assembly/refueling en route. The geolunar shuttle can employ axial or ventral propulsion using current operational single-fuel engines or dual-fuel engines providing enhanced system performance. The geolunar shuttle can be crewed or not, and can be internally configured to carry personnel, cargo, or a mix of both. The geolunar shuttle can optionally be used for low earth orbit and far space, including Earth escape missions.

This invention relates to a propulsion bay to be transported, at least temporarily, in a space launch vehicle and comprising an adapter that co-operates with at least one system located, at least temporarily, on board the bay, said system comprising an electrical power supply. The bay is characterized in that it also comprises at least one electric space propulsion engine that can be powered by the power supply of the system.

Apparatus and methods for controlling a spacecraft for a transfer orbit. The spacecraft includes a momentum subsystem that stores angular momentum relative to a center of mass of the spacecraft, and a propulsion subsystem that includes electric thrusters. A controller identifies a target spin axis for the spacecraft, determines gimbal angles for electric thruster(s) that so that thrust forces from the electric thrusters are parallel to the target spin axis, and initiates a burn of the electric thruster(s) at the gimbal angles. The controller controls the momentum subsystem to compensate for a thruster torque produced by the burn of the electric thrusters. The momentum subsystem is able to produce a target angular momentum about the center of mass, where a coupling between the target angular momentum and an angular velocity of the spacecraft creates an offset torque to counteract the thruster torque.

Elements described herein provide enhancements for spacecraft exploration platforms. In one example, a method of space exploration is provided that includes identifying target objects for approach by a spacecraft, and determining nodal crossings of the target objects with regard to a selected orbital plane about a central body. The method also includes positioning a spacecraft into an initial orbit in the selected orbital plane, determining one or more orbital adjustments for the spacecraft that are restricted to the selected orbital plane to sequentially approach the target objects at the nodal crossings, and approaching the target objects using the one or more orbital adjustments to detect at least a characteristic related to each of the target objects.

A propulsion system for the orbit control of a satellite in Earth orbit driven at a rate of displacement along an axis V tangential to the orbit comprises two propulsion modules, fixed to the satellite, and facing one another relative to the plane of the orbit, each of the propulsion modules comprising, in succession: a motorized rotation link about an axis parallel to the axis V; an offset arm; and a plate supporting two thrusters, suitable for delivering a thrust on an axis, arranged on the plate on either side of a plane P at right angles to the axis V passing through a center of mass of the satellite; each of the two thrusters being oriented in such a way that the thrust axes of the two thrusters are parallel to one another and at right angles to the axis V.

Satellite transfer orbit search methods are described herein. One disclosed example method includes determining, based on boundary transfer orbits of a satellite, end points of an oblate epicycloid segment related to a transfer orbit of the satellite, and calculating, using a processor, a shape of the oblate epicycloid segment based on satellite data and the end points to define a search zone to determine a position of the satellite as the satellite moves along the transfer orbit.