Abstract: An automation system includes a robotic arm with an end effector configured to learn from demonstrations. The automation system receives a demonstration of a lab protocol for operating a type of machine from a user and records a sequence of actions associated with operating the type of machine based on the demonstration. For each action, computer vision is used to derive information associated with the action. The automation system extracts semantic meanings of the action based in part on the information and generates a machine-executable protocol for operating the type of machine by a robot based in part on the semantic meanings of the actions. In some embodiments, the automation system further includes a closed-loop control subsystem that uses computer vision and/or other sensors (e.g., force torque sensors) to automatically maintain a desired state or set point associated with operation of the type of machine.

Abstract: An electric propulsion (EP) device is used to enable, a stationkeeping satellite to track a prescribed stationkeeping Earth orbit. EP propellant and electric power are throttled to vary the thrust and specific impulse of the EP device. A solar array provides electrical power during each Earth day cycle with excess power above that needed by the spacecraft stored by a battery. Software control manages the voltage, current and burn time to minimize propellant usage and impact to the system.

Abstract: An electric propulsion (EP) device is used to enable a stationkeeping satellite to track a prescribed stationkeeping Earth orbit. EP propellant and electric power are throttled to vary the thrust and specific impulse of the EP device. A solar array provides electrical power during each Earth day cycle with excess power above that needed by the spacecraft stored by a battery. Software control manages the voltage, current and burn time to minimize propellant usage and impact to the system.

Abstract: A spacecraft, such as a geosynchronous weather or communications satellite, is constructed to include a plurality of low thrust thrusters mounted at predetermined locations on at least one of a spacecraft appendage or a spacecraft bus. The plurality of low thrust thrusters are fired in pairs for at least one of removing a disturbance torque or providing fine pointing attitude control. In one embodiment the low thrust thrusters are mounted on a solar array panel, thereby increasing the moment arm and enhancing the thrust output of the low thrust thrusters. In one embodiment a spacecraft has a plurality of low thrust thrusters arranged as at least two sets of two low thrust thrusters, individual ones of the low thrust thrusters of a set being disposed in a V-configuration and mounted at predetermined locations on at least one of a spacecraft appendage or a spacecraft bus. The plurality of low thrust thrusters are selectively fired for achieving control of 3-axes of spacecraft attitude or momentum.