초록 ▼

A spacecraft includes an articulating sunshield assembly 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 that can be controllably positioned as the spacecraft orbits about a

A spacecraft includes an articulating sunshield assembly 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 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.

대표청구항 ▼

1. A method for deploying at least a first shield member connected to a spacecraft body, comprising:providing a spacecraft that includes a spacecraft body and at least a first shield member connected to said spacecraft body; and deploying said first shield member relative to said spacecraft body in

1. A method for deploying at least a first shield member connected to a spacecraft body, comprising:providing a spacecraft that includes a spacecraft body and at least a first shield member connected to said spacecraft body; and deploying said first shield member relative to said spacecraft body in space including substantially co-locating a center of mass of said spacecraft with a solar radiation center of pressure in each of a pitch direction, a yaw direction and a roll direction by at least using movement of at least first portions of said first shield member about at least one of a pitch axis, a yaw axis and a roll axis to achieve a neutral stability condition of said spacecraft, said center of pressure indicating substantially a point on said spacecraft about which effective solar pressures are balanced.