Abstract: A satellite power distribution method for efficiently distributing power to satellite electric propulsion thrusters (24) is provided. The satellite includes spacecraft loads (20), an electric propulsion thruster (24), thruster auxiliary circuits (22), and a first power transformer (30). The first power transformer (30) has a primary winding (32) coupled to a first energy source (12) that supplies satellite power. A first secondary winding (36) of the first power transformer (30) is coupled to the spacecraft loads (20) for supplying primary power. The power distribution method includes the steps of first coupling a second secondary winding (34) to the first power transformer (30) for converting the satellite power to thruster discharge power which is rectified. The rectified discharge power is filtered to obtain power that is supplied to the electric propulsion thruster (24). Finally, satellite power is converted to auxiliary power for powering the thruster auxiliary circuits (22).

Abstract: A satellite power distribution method for efficiently distributing power to satellite electric propulsion thrusters (24) is provided. The satellite includes spacecraft loads (20), an electric propulsion thruster (24), thruster auxiliary circuits (22), and a first power transformer (30). The first power transformer (30) has a primary winding (32) coupled to a first energy source (12) that supplies satellite power. A first secondary winding (36) of the first power transformer (30) is coupled to the spacecraft loads (20) for supplying primary power. The power distribution method includes the steps of first coupling a second secondary winding (34) to the first power transformer (30) for converting the satellite power to thruster discharge power which is rectified. The rectified discharge power is filtered to obtain power that is supplied to the electric propulsion thruster (24). Finally, satellite power is converted to auxiliary power for powering the thruster auxiliary circuits (22).

Abstract: A satellite power regulation and pointing system is disclosed that comprises a power bus (104) and first and second flywheels (114-116) capable of storing rotational energy. Each flywheel (114-118) comprises a flywheel motor/generator (202) for increasing the rotational energy in its associated flywheel when storing power in its associated flywheel and for reducing the associated flywheel rotational energy when drawing power from its associated flywheel. The system also includes individual flywheel regulators (108-112) connected to the power bus (104) and to the flywheel motor/generators (202). Each flywheel regulator (108-112) includes a power control circuit (204) that allows power to flow to a flywheel motor/generator (202) from the power bus (104) during an energy storage period and that allows power to flow to the power bus (104) from the flywheel motor/generator (202) during an energy drawing period.

Abstract: A solar array maximum power point tracking system for regulating the power output of a solar array associated with a spacecraft. An on-board computer measures the bus voltage and current from the solar array and generates a power calculation of the solar array power output. The on-board computer applies a first reference signal to a remote error amplifier representative of an incremental change in the solar array power. Additionally, the solar array bus voltage is applied to the remote error amplifier such that the remote error amplifier senses the solar array bus voltage and generates an output voltage indicative of the change of the solar array power. The output voltage of the error amplifier is applied to a power processor unit. The output voltage from the remote error amplifier and the bus voltage are applied to a power stage within the power processor unit. The power stage generates an output current that is applied to an arcjet thruster.

Abstract: A system for supplying d.c. power to an electrical load, in which such load includes a rechargeable battery, is characterized by a plurality of power sources connected in common to the electrical load, wherein the current generated by the multiple power sources is combined to supply such electrical load. Each of the power sources includes a solar panel and a controlled variable transconductance device, such as a Buck converter, connected in electrical series circuit. A digital processor, including a stored program, coupled to the control inputs of the variable transconductance devices, selectively individually sets the duty cycle of each transconductance device under control of a stored program, whereby the electrical power supplied by said power sources to said electrical load is individually controlled by the digital processor.