An attitude control system for a satellite having a pitch, roll, and yaw axis, each axis, being mutually perpendicular to the other axes comprising:
- a. three or more reaction wheels mounted on respective axes in fixed angular relation to said three perpendicular axes,
- b. attitude sensing means for determining the angular deviation of the satellite from a predetermined reference attitude, said sensing means including a sensor for generating attitude error signals relative to the earth, said sensing means further including at least two sun sensors for generating attitude error signals relative to the sun,
- c. means for providing data signals corresponding to orbit ephemeris,
- d. means responsive to said sun attitude error signals and said ephemeris data signals for computing attitude errors of said yaw axis relative to the sun,
- e. control means responsive to said earth attitude error signals and said sun attitude error signals for controlling the angular velocity of said wheels such that the respective attitude errors signals converge to zero,
- f. control means responsive to the angular velocity of each of said wheels for controlling the velocity of said wheels such that the long time-average momentum along said roll and yaw axes is essentially zero, and a residual momentum bias is generated along said pitch axis to provide
- gyroscopic stiffness to said satellite. 2. A system according to claim 1 including torquing means wherein said velocity control means includes desaturation means responsive to the speed of said wheels for energizing said torquing means to exert external torques on said satellite such that the velocity of said wheels is maintained within predetermined ranges of
- velocity. 3. A system according to claim 2 wherein said torquing means
- comprise thrusters. 4. A system according to claim 2 wherein said torquing
- means comprise magnetic torquers. 5. A system according to claim 1 wherein said yaw attitude error computing means includes switch means for rendering said computer means inoperative during portions of an orbit of said satellite wherein the angle between the sun line and said yaw axis is less than a prescribed threshold, and, further, wherein said control means includes means for controlling the velocity of said wheels such that the momentum along said yaw axis is controlled to a predetermined schedule.
- A system according to claim 1 wherein said earth sensing means is a
- horizon sensor. 7. A system according to claim 1 wherein said attitude
- sensing means comprises one or more accelerometers. 8. A system according to claim 1 wherein said earth sensing means comprises a receiver of radio
- beacon signals transmitted from the earth. 9. A system according to claim 1 wherein three reaction wheels only are mounted in mutually orthogonal relation and aligned respective to said roll, pitch, and yaw axes, the velocity of said yaw wheel being controlled in response to said sun sensor signals and the velocity of said roll and pitch wheels being conrolled in
- response to said earth sensor signals. 10. A system according to claim 1 wherein four wheels only of said reaction wheels are mounted in skewed relation to said roll, yaw, and pitch axes, the respective velocities of each of said wheels being controlled such that the long time average vectorial sum of the angular momenta along said roll and yaw axes is essentially zero, and the long time average vector sum of the angular momentum along the pitch axis is offset by a predetermined bias momentum magnitude, the individual wheel speeds being so-controlled that no wheel either reverses direction or operates near zero speed but rather operates
- at an average bias speed. 11. A system according to claim 10 including torquing means wherein said control means includes desaturation means responsive to the speed of said wheels for energizing said torquing means to exert external torques on said satellite such that the velocity of said
- wheels is maintained within predetermined ranges of velocity. 12. A system according to claim 1 wherein one or more of said wheels is normally inoperative, further including means for rendering operative said normally inoperative wheel when any one of said remaining wheels is rendered
- inoperative. 13. A method for controlling the attitude of an orbiting satellite, said satellite having pitch, roll, and yaw body axes, and three or more reaction wheels mounted on respective axes in fixed angular relation to said body axes, comprising the steps of:
- a. sensing errors in deviation of said satellite from a reference attitude relative to the earth and the sun,
- b. controlling the velocity of said wheels in response to said attitude errors such that the long time average vectorial sum of the angular momenta along the roll and yaw axes is essentially zero and the long time average vector sum of the angular momentum along said pitch axis is offset
- by a predetermined bias magnitude. 14. The method according to claim 13 further including the step of:
- desaturating the respective momentum of each of said wheels such that the velocity of said wheels is maintained within predetermined ranges of
- velocity. 15. The method according to claim 14 further including the step of:
- modifying the velocity of said wheels when the angle between the sun line and said yaw axis is less than a predetermined amount such that the momentum along said yaw axis is controlled to a predetermined schedule.
- The method according to claim 13 wherein one or more of said wheels is normally inoperative, further including the step of:
- rendering operative said normally inoperative wheel when one of the remaining wheels is rendered inoperative.