Abstract: Various embodiments of the present technology generally relate to devices and methods for generating and directing energetic electrons toward a target. More specifically, some embodiments relate to devices, systems, and methods for generating and directing energetic electrons based in the photoelectric effect and directing electric field-focused beams of the energetic electrons toward a target. Electron guns according to the present technology include one or more light sources to stimulate electron transmission, and a series of differentially charged stages to provide a hollow path allowing electrons generated by the photoelectric effect of the light irradiated on interior surfaces defining the path through the stages to travel to an exit of the electron gun. Each of the differentially charged stages have a different potential, thereby providing electrons having two or more different and tunable energy levels exiting as a beam from the electron gun.

Abstract: A magnetic buoyancy enhanced electrolysis system includes a water pump, an electrolysis cell, a magnetic phase separator, and a plurality of conduits configured to facilitate fluid communication between the water pump, the electrolysis cell, and the magnetic phase separator. The electrolysis cell includes an electrode and one or more magnets that cause gas bubbles to detach from the electrode to create a two-phase flow of water and the gas bubbles. The phase separator includes one or more magnets that collect the gas bubbles from the two-phase flow.

Abstract: Various embodiments of the present technology generally relate to devices and methods for generating and directing energetic electrons toward a target. More specifically, some embodiments relate to devices, systems, and methods for generating and directing energetic electrons based in the photoelectric effect and directing electric field-focused beams of the energetic electrons toward a target. Electron guns according to the present technology include one or more light sources to stimulate electron transmission, and a series of differentially charged stages to provide a hollow path allowing electrons generated by the photoelectric effect of the light irradiated on interior surfaces defining the path through the stages to travel to an exit of the electron gun. Each of the differentially charged stages have a different potential, thereby providing electrons having two or more different and tunable energy levels exiting as a beam from the electron gun.

Abstract: Space tug vehicles and methods for providing space tugs and moving target vehicles are provided. More particularly, a space tug utilizing electrostatic or Coulomb force for acting on target vehicles and for moving the target vehicles into new orbits or altitudes are provided. The space tug may establish an attractive electrostatic force by controlling the electrical potential of the space tug so that it is opposite the electrical potential of a target vehicle. The target vehicle may acquire an absolute electrical potential due to its interaction with the space plasma and photoelectrons or the space tug may impart additional charge to the target vehicle. After establishing the attractive electrostatic force, a propulsion system of the space tug is operated to provide thrust. Thrust is directed to change the orbit and/or position of the target vehicle that is being pulled towards the space tug by the electrostatic force.

Abstract: Spacecraft vehicles and methods for providing reorbiters capable of moving target objects are provided. More particularly, a reorbiter utilizing electrostatic or Coulomb force for acting on target objects and for moving the target objects into new orbits or altitudes are provided. The reorbiter may establish an electrostatic force by controlling the electrical potential of the reorbiter through active charge emission. The target object may acquire an electrical potential due to its interaction with the space plasma and photoelectrons or the reorbiter may impart additional charge to the target object. After establishing the electrostatic force, a propulsion system of the reorbiter is operated to provide thrust. Thrust is directed to change the orbit and/or position of the target object that is being moved by the electrostatic force between the reorbiter and the target object.

Abstract: Space tug vehicles and methods for providing space tugs and moving target vehicles are provided. More particularly, a space tug utilizing electrostatic or Coulomb force for acting on target vehicles and for moving the target vehicles into new orbits or altitudes are provided. The space tug may establish an attractive electrostatic force by controlling the electrical potential of the space tug so that it is opposite the electrical potential of a target vehicle. The target vehicle may acquire an absolute electrical potential due to its interaction with the space plasma and photoelectrons or the space tug may impart additional charge to the target vehicle. After establishing the attractive electrostatic force, a propulsion system of the space tug is operated to provide thrust. Thrust is directed to change the orbit and/or position of the target vehicle that is being pulled towards the space tug by the electrostatic force.

Abstract: Spacecraft vehicles and methods for providing reorbiters capable of moving target objects are provided. More particularly, a reorbiter utilizing electrostatic or Coulomb force for acting on target objects and for moving the target objects into new orbits or altitudes are provided. The reorbiter may establish an electrostatic force by controlling the electrical potential of the reorbiter through active charge emission. The target object may acquire an electrical potential due to its interaction with the space plasma and photoelectrons or the reorbiter may impart additional charge to the target object. After establishing the electrostatic force, a propulsion system of the reorbiter is operated to provide thrust. Thrust is directed to change the orbit and/or position of the target object that is being moved by the electrostatic force between the reorbiter and the target object.

Abstract: A noncontact position and orientation measurement system includes at least four beacons disposed on a first object. Each beacon is operable to generate an optical signal. The system also includes a beacon controller operable to sequentially activate and deactivate each of the beacons. The system also includes an electro-optical sensor disposed on a second object. The electro-optical sensor is operable to generate an output signal for each optical signal received from the beacons. The system further includes a signal con-roller coupled to the electro-optical sensor. The signal controller is operable to determine a position and an orientation of the second object relative to the first object using the output signals generated by the electro-optical sensor.