Attitude control device using solar sails for a satellite stabil

Details Attitude control device using solar sails for a satellite stabil Attitude control device using solar sails for a satellite stabil

1990-12-21

1992-07-28

Peters, Jr., Joseph F.

Aeronautics and astronautics

Spacecraft

With payload accommodation

244168, 136244, B64G 144

Patent

active

051335182

ABSTRACT:
An attitude control device for a satellite stabilized on three axes including a pitch axis comprises two solar generator wings extending in opposite directions away from a satellite body on respective longitudinal axes at least approximately parallel to the pitch axis. Two drive motors drive these wings independently of each other in rotation about rotation axes at least approximately parallel to the pitch axis to keep the wings facing the Sun with a depointing angle at most equal to a predetermined maximum depointing value. Sensors measure attitude angles and a computation system commands the drive motors according to the attitude angles. On each wing an additional surface in the form at least one vane extends longitudinally beyond the end of the wing parallel to its longitudinal axis. These additional surfaces have substantially the same surface area and are inclined about this axis relative to the wings in opposite directions by at least approximately the same angle which is less than the 90.degree. complement of the maximum amplitude of wing depointing.

REFERENCES:
patent: 3304028 (1967-02-01), Nicklas et al.
patent: 3339863 (1967-09-01), Nicklas et al.
patent: 4262867 (1981-04-01), Piening
patent: 4426052 (1984-01-01), Hubert et al.
patent: 4988060 (1991-01-01), Janson et al.

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