초록 ▼

A spacecraft (10) body (20) located in an external magnetic field (12) has a substantially unbalanced electrical power bus (18) that generates a composite local magnetic field The electrical power bus (18) substantially surrounds an external surface (22) of the spacecraft (10). Current in the electr

A spacecraft (10) body (20) located in an external magnetic field (12) has a substantially unbalanced electrical power bus (18) that generates a composite local magnetic field The electrical power bus (18) substantially surrounds an external surface (22) of the spacecraft (10). Current in the electrical power bus (18) is solar panel (14and 16) and/or battery (34) generated and can flow in different directions through different current paths. Electrical loads (58) are coupled to power converters (56) and current path switches (54) to couple the power converters (56) to the various current paths. A controller (28) takes sensor data (82), determines a required attitude adjustment torque (84), translates that adjustment torque into a composite magnetic field (86), determines an unbalanced bus current profile (88) to generate that composite magnetic field, selects a current source (90) and regulates current path switches (92) to achieve a desired attitude adjustment torque for the spacecraft (10).

대표청구항 ▼

[ What is claimed is:] [1.] An attitude control system for a spacecraft said attitude control system comprising:an first electrical power bus configured to supply power to a plurality of electrical loads of said spacecraft and further configured to generate a first local magnetic field which interac

[ What is claimed is:] [1.] An attitude control system for a spacecraft said attitude control system comprising:an first electrical power bus configured to supply power to a plurality of electrical loads of said spacecraft and further configured to generate a first local magnetic field which interacts with an external magnetic field; anda controller coupled to said first electrical power bus, said controller being configured to manage said first electrical power bus to control said first local magnetic field such that interaction between said first local magnetic field and said external magnetic field adjusts attitude of said spacecraft.