Momentum biased satellite attitude stabilization using Pd controller with fuzzy gain adjustment

Abstract EN

Momentum biased satellites are dual spin satellites in which constant angular momentum is provided by a momentum wheel.

The momentum bias is not sufficient to stabilize completely the momentum axis in space.

Active control is used to assure accurate attitude stabilization.

Control of the roll and yaw angles with and without yaw measurement will be analyzed.

Control engineers prefer not to use angular rate sensors except for very special tasks and for short periods.

The rate of Euler angles will be obtained by differentiation, with the adequate noise filters.

Fuzzy gain adjustment is used for the case of momentum biased satellites without yaw measurement in order to minimize error.

The gain, output scaling factor, of the controller is adjusted on line according to the current states of the controlled process.