A method of moving a spacecraft from an initial orbit to a final orbit includes providing a spacecraft with thrusters traveling in an initial orbit that has a first RAAN. Thrusters are activated to move the spacecraft into a transfer orbit having more eccentricity than the initial orbit. A RAAN of the transfer orbit changes over time toward a target RAAN. The spacecraft enters an aerobraking orbit wherein the spacecraft is exposed to increased atmospheric drag to reduce orbit energy and reduce an apoapsis radius. Thrusters may be activated to increase the periapsis radius of the aerobraking orbit and cause the spacecraft to move into the final orbit, the final orbit having a final RAAN different from the first RAAN.

A method of moving a spacecraft from an initial orbit to a final orbit includes providing a spacecraft with thrusters traveling in an initial orbit that has a first RAAN. Thrusters are activated to move the spacecraft into a transfer orbit having more eccentricity than the initial orbit. A RAAN of the transfer orbit changes over time toward a target RAAN. The spacecraft enters an aerobraking orbit wherein the spacecraft is exposed to increased atmospheric drag to reduce orbit energy and reduce an apoapsis radius. Thrusters may be activated to increase the periapsis radius of the aerobraking orbit and cause the spacecraft to move into the final orbit, the final orbit having a final RAAN different from the first RAAN.

A magnetohydrodynamic (MHD) flow control mechanism is described which substantially improves the existing processes in that smaller magnetic fields, requiring far less mass, are placed away from the forebody of the spacecraft to produce Lorentz forces that augment the lift and the drag forces for guidance, navigation, and control of the spacecraft.

A satellite deorbiting device including an aerobraking surface including a satellite attitude control device with gravity gradient, the device with gravity gradient including at least one mast carrying the aerobraking surface, a first end of which is secured to the satellite and the second end of which is provided with a mass, such that the mast is oriented in a direction opposing that of the planet around which the satellite orbits.

A device to stabilize and deorbit a satellite includes a pair of coplanar masts, each one carrying at least one membrane forming an aerobraking web. The masts are fixed to the satellite along non-parallel axes. Each mast is provided on the opposite end of the satellite with a mass to generate a gravity gradient. The end of each mast is fixed to the satellite. The masts form, with the bisectrix between the masts, a fixed angle to align the bisectrix with the satellite speed vector at any altitude.

A magnetohydrodynamic (MHD) flow control mechanism is described which substantially improves the existing processes in that smaller magnetic fields, requiring far less mass, may be placed away from the forebody of the spacecraft to produce Lorentz forces that augment the lift and the drag forces for guidance, navigation, and control of the spacecraft. The MHD flow control mechanism may also be configured to provide additional thermal protection of the electrodes therein.

A stage of a rocket is disclosed. The rocket stage may include: a body, and a plurality of foldable propulsion units spaced around a circumference of the body, where each propulsion unit comprises: a folding beam; at least one motor mounted to the folding beam, and at least one propeller mounted to the at least one motor, configured to generate a thrust to propel the rocket.