A method of de-spinning a rotor of a propulsion system includes providing one or more spinning rotors rotatably mounted on a frame with a bearing having a bearing outer race, bearing balls, and bearing inner race; providing a force mechanism coupled with the one or more spinning rotors for applying a load to the one or more spinning rotors; and loading an outer portion of the outer bearing race, bearing ball, and inner bearing race of the bearing, a load on the outer portion of the bearing race, bearing ball, and inner bearing race of the bearing corresponding to a force applied to the one or more spinning rotors by the drive mechanism. The one or more spinning rotors de-spin at a rate corresponding to the load on the bearing balls.

There is disclosed a vehicle and a method for propelling the vehicle comprising a propulsion arrangement. The propulsion arrangement includes a chamber arrangement that is configured to store antimatter therein by using magnetic and/or electrostatic fields. The chamber arrangement and a centre of gravity of the vehicle are positioned at a relative distance from each other to form a matter-antimatter dipole when in operation. The matter-antimatter dipole provides a propulsion force to the vehicle. Optionally, the vehicle is a space vehicle (namely a spacecraft, a satellite or similar).

A magnetic field propulsion unit includes a magnetic field generating device with multiple conductive lines conduct a current to generate a magnetic field; a contact breaker arrangement individually transitions each of the multiple conductive lines from a conductive state to a non-conductive state; an energy supply unit provides the magnetic field generating device with electrical energy; and a control unit controls the energy supply unit so that energy supply to each individual conductive line is controlled and control the contact breaker arrangement. The multiple conductive lines are arranged along a longitudinal axis. The control unit supplies a first conductive line with electrical energy so that a first magnetic field surrounding the first conductive line is generated, transitions the first conductive line to a non-conductive state, and supplies a second conductive line with electrical energy so that a second magnetic field is generated.

Omnivorous solar thermal thrusters and adjustable cooling structures are disclosed. In one aspect, a solar thermal rocket engine includes a solar thermal thruster configured to receive solar energy and one or more propellants, and heat the one or more propellants using the solar energy to generate thrust. The solar thermal thruster is further configured to use a plurality of different propellant types, either singly or in combination simultaneously. The solar thermal thruster is further configured to use the one or more propellants in both liquid and gaseous states. Related structures can include valves and variable-geometry cooling channels in thermal contact with a thruster wall.

A method of generating a momentum change in a vehicle by phase changing matter in a closed system is used to change the momentum of the vehicle without the need of a combustion system for propulsion. The method uses the multi-phase dynamics of fluidic matter to create a momentum differential within a closed system that results in a momentum excess that changes the overall momentum of the system. The change of the overall momentum of the system results in a change in motion of the vehicle. The momentum differential is achieved by phase changing the fluidic matter moving through a heat exchanger. The phase change of the fluidic matter is arranged so that the momentum of the fluidic matter is reduced as the fluidic matter leaves the heat exchanger. The reduction in momentum of the fluidic matter results in the momentum differential that changes the overall momentum of the system.

A solar panel module includes a solar panel; a printed circuit board combined with a plane of the solar panel and including a microchamber and an ignition circuit; and a propellent inserted into the microchamber and connected to the ignition circuit.

A novel cooling system for a superconducting electromagnet (740) that is suitable for use in satellite (700), or at least one or more components of the electromagnet (740) is disclosed. A satellite (700) and electromagnetic control system (705) for position control of such a satellite (700) are also disclosed. In one embodiment, the superconducting magnet control system (705) comprises at least one superconducting electromagnet (740) with at least one cooling element and at least one cryocooler (735). The cryocooler (735) is thermally coupled with the cooling element thereby enabling cooling of the superconducting electromagnet (740) or at least one or more components thereof through the cooling element solely by conduction cooling.

A propulsion method includes: providing a pair of synchronized rotors rotatably mounted on a frame with a bearing having a bearing outer race, bearing balls, and bearing inner race; providing a plurality of permanent magnets mounted on the pair of synchronized rotors; rotating the pair of synchronized rotors such that one of the pair of synchronized rotors rotates in a clockwise direction and the other of the pair of synchronized rotors rotates in a counterclockwise direction; loading an outer portion of the outer bearing race, bearing ball, and inner bearing race of each of the bearings, a load on the outer portion of the bearings corresponding to an attractive force between the permanent magnets of the pair of synchronized rotors. A thrust is imparted on the frame in a direction corresponding to a direction of loading of the inner bearing race.

ThermaSat™ propulsion system uses water as a safe and non-explosive propellant, and which is unpressurized at liftoff. Utilizing solar thermal propulsion, the compact and efficient capacitor heats water to steam to produce high thrust and total impulse. The advanced optical system allows for the thermal capacitor to charge through solar power alone with no protruding concentrators or power draw from the main bus. Additional solar panels, body mounted to the ThermaSat, provide auxiliary heating of the thermal capacitor when not directly incident to sunlight to promote non-sun pointing operations.

Methods of launching a vehicle using impulsive force are disclosed. In one instance, a vehicle is launched easterly with impulsive force in a plane corresponding to the vehicle's elliptical orbital path. In another instance, a method of closing a timing difference is disclosed. The vehicle undergoes a series of forces after impulsive launch. The first force establishes an orbit having a period significantly different from the orbital period of a satellite or desired vehicle location, closing the difference in an integer number of orbits. The second force establishes the vehicle in circular orbit with the satellite or desired vehicle location. In another instance, the vehicle launched impulsively from a first celestial body travels a first path, and the vehicle experiences a second force along a hyperbolic path about the second celestial body and enters circular orbit about the second celestial body.