Abstract: A long endurance powered aircraft includes a fuselage, a propeller coupled to the fuselage, a wing coupled to the fuselage, and an energy storage system disposed within the fuselage. The wing includes an adjustable surface area including solar cells configured to collect incident solar energy and convert the collected incident solar energy to electrical energy for powering the aircraft during daylight flight. The energy storage system is configured to convert excess electrical energy converted from collected incident solar energy to chemical energy, store the chemical energy, and convert the stored chemical energy to electrical energy for powering the aircraft during night flight.

Abstract: An electrodynamic method includes providing an electrodynamic structure with a periphery, providing power, collecting electrons, and emitting electrons. The emitting electrons and the collecting electrons utilizes at least 20% of the periphery of the electrodynamic structure. The method includes conducting current to provide at least one of electrodynamic propulsion and power generation.

Abstract: An electrodynamic method includes providing an electrodynamic structure with a periphery, providing power, collecting electrons, and emitting electrons. The emitting electrons and the collecting electrons utilizes at least 20% of the periphery of the electrodynamic structure. The method includes conducting current to provide at least one of electrodynamic propulsion and power generation.

Abstract: An electrodynamic structure having a periphery. The electrodynamic structure includes a power system, a plurality of collectors, a plurality of emitters, and conductive paths. The plurality of collectors are disposed on the periphery of the electrodynamic structure and configured to collect electrons. The plurality of emitters are disposed on the periphery of the electrodynamic structure and configured to emit electrons. At least 20% of the periphery of the electrodynamic structure is utilized for electron collection and electron emission. The conductive paths are configured to conduct current between the power system, the collectors, and the emitters to provide at least one of power generation and electrodynamic propulsion.

Abstract: The present invention improves the orbital maneuvering and power generation capabilities of a system of a satellite(s) connected with a conducting tether(s) by spinning the system about its mass center at an angular rate which is relatively high compared to the average orbital rate. An improvement in tether performance is achieved because at many times during rotation the tether is positioned at much better angles with the magnetic field and significantly higher currents are driven through the tether without destabilizing the system. The current can flow either in the direction of the EMF induced in the tether, or in the reverse direction, depending on the tether orientation with respect to the magnetic field and the mission goals. The reverse current is driven by the onboard power sources. Spinning electrodynamic tether systems can also be lighter and simpler in design and more flexible in operation.