A system and method are provided for operating a control moment gyro (CMG) in a spacecraft. The CMG includes a spin motor, and a CMG rotor that is coupled to the spin motor and is configured to rotate about a spin axis. Electrical power from a power source is supplied to the spin motor to rotate the CMG rotor about the spin axis. A determination is made as to whether the power source can supply sufficient electrical power to the spin motor. If the power source cannot supply sufficient electrical power to the spin motor, the spin motor is rotated by the CMG rotor to generate and supply electrical power to the power source.

 
Web www.patentalert.com

< Method and system for providing cruciform steered, bent biconic and plasma suppression for maximum accuracy

< Systems and methods for controlling flows with electrical pulses

> Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods

> Aerospace vehicle fairing systems and associated methods
~ 00609