| 摘要 |
PROBLEM TO BE SOLVED: To provide a system and a method for gyroless transfer orbit sun acquisition using only wing current measurement feedback so that a spacecraft is able to maneuver itself to orient its solar panel to its maximum solar exposure spinning attitude. SOLUTION: The system and method involve controlling a spacecraft maneuver using only the solar wing current feedback as the sole closed-loop feedback sensor for attitude control. A spin controller is used for controlling the spacecraft spin axis orientation and spin rate. The spin controller commands the spacecraft spin axis orientation to align with an inertial fixed-direction and to rotate at a predetermined spin rate by using a momentum vector. In addition, a method for estimating spacecraft body angular rate and spacecraft attitude uses a combination of solar array current and spacecraft momentum as the cost function with the solar wing current feedback as the only closed-loop feedback sensor. COPYRIGHT: (C)2011,JPO&INPIT |
