| 摘要 |
A spacecraft (10) includes an articulating sunshield assembly (12) that is capable of simultaneously performing thermal control functions and solar torque balancing for the spacecraft. The sunshield assembly includes a pair of shield members (12a, 12b) that can be controllably positioned as the spacecraft orbits about a primary body. Control functionality is provided for periodically adjusting the positions of the shield members to maintain a neutral solar torque stability condition for the spacecraft. In one embodiment, solar torque balancing is performed in each of three independent rotational directions or planes (i.e., roll, pitch, and yaw) using the sunshield assembly. Functionality is also provided for performing momentum dumping tasks using the sunshield assembly in place of, or in conjunction with, on-board thrusters. |
