| 摘要 |
A stabilization system (40) for a spacecraft which enables the spacecraft to be stabilized by rotation about any principal moment of inertia axis (x, y). The system includes two pairs of control thrusters (14, 16; 18, 20) for producing positive and negative control moments about two orthogonal axes (x, y) mutually perpendicular to the axis of rotation of the spacecraft. The control system (40) includes rate gyros (42, 46) which provide error signals which are sent to duty cycle modulators (54). The duty cycle modulators (54) provide a pulse width modulated control signal to the control thrusters (14 - 20) to approximate proportional control of spacecraft attitude. |
