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. The output current is also applied to a transconductive circuit that converts the output current to a voltage so as to condition the input voltage to the power stage.
Abstract:
A control circuit (33) controls the gain of a torque sensor (32) of a type providing two output signals (V.sub.02, V.sub.03) where the two output signals have values functionally related to a value of an input drive signal (V.sub.D) and torque sensed by the torque sensor. The two values varies substantially equally and oppositely from each other in response to sensed torque. A variable gain amplifier (36) provides the input drive signal. A rectifiers/filters circuit (38) monitors the two output signals of the torque sensor. A gain control circuit (50) controls the gain of the drive signal in response to the sum of the monitored two output signals of the torque sensor relative to a reference voltage.