초록 ▼

A method is provided for controlling the attitude of a momentum biased spacecraft about all three mutually orthogonal axes during a thruster firing maneuver without separately sensing angular displacement, angular rate, or angular acceleration about the spacecraft yaw axis. The method includes a tra

A method is provided for controlling the attitude of a momentum biased spacecraft about all three mutually orthogonal axes during a thruster firing maneuver without separately sensing angular displacement, angular rate, or angular acceleration about the spacecraft yaw axis. The method includes a transient phase during which a yaw feedforward torque is computed based on the known pitch/yaw coupling due to thruster geometry, and a steady state phase, during which feedback gains are adjusted to estimate yaw attitude based on coupling of a steady state disturbance torque about the roll axis of the spacecraft and a steady state disturbance torque about the yaw axis of the spacecraft.

대표청구항 ▼

[ We claim:] [1.]1. A method of controlling the attitude of a momentum biased spacecraft about three mutually orthogonal axes during a thruster firing maneuver without separately sensing angular displacement, angular rate, or angular acceleration about one of the three mutually orthogonal axes, the

[ We claim:] [1.]1. A method of controlling the attitude of a momentum biased spacecraft about three mutually orthogonal axes during a thruster firing maneuver without separately sensing angular displacement, angular rate, or angular acceleration about one of the three mutually orthogonal axes, the spacecraft including a pitch axis, a roll axis, and a yaw axis, the method comprising the steps of:estimating torques applied by each thruster fired during the maneuver, including torques applied by the thrusters that result from thruster aiming errors or unknown center of mass motion;predicting environmental disturbance torques in pitch as well as roll/yaw;estimating spacecraft attitude and rotational rate about the unmeasured axis; andemploying feedback to correct pointing error caused by thruster torques and environmental disturbance torques.