Einzeltreffer — DigiBib

A momentum-control system for a spacecraft is disclosed. The momentum-control system comprises an attitude-control system. The attitude-control system receives data concerning a desired spacecraft maneuver and determines a torque command to complete the desired spacecraft maneuver. A momentum actuator control processor coupled to the attitude-control system receives the torque command. The momentum actuator control processor calculates a gimbal rate command comprising a range-space gimbal rate required to produce the torque command and a null-space gimbal rate required to maximize the ability to provide torque in the direction of a current torque. At least four control-moment gyros are coupled to the momentum control actuator control processor. Each of the control-moment gyros receives and executes the gimbal rate to produce the desired maneuver.

Titel:	METHOD AND SYSTEM FOR OPTIMIZING TORQUE IN A CMG ARRAY
Autor/in / Beteiligte Person:	Peck, Mason A. ; Hamilton, Brian J. ; Underhill, Brian
Link:	View record in USPTO Patent Applications (Volltext)
Veröffentlichung:	2006
Medientyp:	Patent
Sonstiges:	Nachgewiesen in: USPTO Patent Applications Sprachen: English Document Number: 20060022091 Publication Date: February 2, 2006 Appl. No: 10/903774 Application Filed: July 30, 2004 Claim: 1. A method for optimizing torque in a CMG array of a spacecraft comprising: receiving a torque command representing a desired torque to produce an attitude adjustment for the spacecraft; computing a range-space gimbal rate required to produce the desired torque; computing a null-space gimbal rate required to maximize the ability to provide torque in a chosen direction; computing a total gimbal rate by summing the range-space gimbal rate and the null-space gimbal rate; and providing commands to the CMGs to produce the total gimbal rate. Claim: 2. The method of claim 1 wherein the step of computing a null-space gimbal rate further comprises computing a null-space gimbal rate based on the projection of a gimbal rate that produces a momentum vector perpendicular to the current direction of the torque onto the null space of the array Jacobian. Claim: 3. The method of claim 1 further comprising: computing a gimbal rate that avoids singularities in three dimensions; and determining an optimal combination of the gimbal rate required to maximize momentum in the direction of current torque and the gimbal rate that avoids singularities in three dimensions. Claim: 4. The method of claim 3 wherein the step of computing a gimbal rate that avoids singularities in three dimensions further comprises computing a null-space gimbal rate based on the projection of the determinant of the product of a Jacobian matrix and the transpose of the Jacobian matrix. Claim: 5. The method of claim 3 wherein the step of computing a gimbal rate that avoids singularities in three dimensions further comprises computing a null-space gimbal rate based on the projection of the eigenvalues of the product of a Jacobian matrix and the transpose of the Jacobian matrix. Claim: 6. A momentum-control system for a spacecraft comprising: an attitude-control system operable to receive data concerning a desired spacecraft maneuver and determine a torque command to complete the desired spacecraft maneuver; a momentum actuator control processor coupled to the attitude-control system and operable to receive the torque command and calculate a gimbal rate command comprising a range-space gimbal rate required to produce the torque command and a null-space gimbal rate required to maximize the ability to provide torque in a chosen direction; and a CMG array comprising at least four control-moment gyros, each CMG operable to receive the gimbal rate command and execute the gimbal rate command to produce the desired maneuver. Claim: 7. The momentum-control system of claim 6 wherein the null-space gimbal rate is calculated based on the projection of a gimbal rate that produces a momentum vector perpendicular to the current direction of the torque onto the null space of the array Jacobian. Claim: 8. The momentum-control system of claim 6 wherein the momentum actuator control processor is further operable to: compute a gimbal rate that avoids singularities in three dimensions; and determine an optimal combination of the gimbal rate command required to maximize momentum in the direction of current torque and the gimbal rate that avoids singularities in three dimensions. Claim: 9. The momentum-control system of claim 8 wherein the gimbal rate that avoids singularities in three dimensions is determined by computing a null-space gimbal rate based on the projection of the determinant of the product of a Jacobian matrix and the transpose of the Jacobian matrix. Claim: 10. The momentum-control system of claim 8 wherein the gimbal rate that avoids singularities in three dimensions is determined by computing a null-space gimbal rate based on the projection of the eigenvalues of the product of a Jacobian matrix and the transpose of the Jacobian matrix. Claim: 11. A method for maximizing the ability to provide torque in a chosen direction of a CMG array in a spacecraft while avoid singularities when maneuvering the spacecraft comprising: computing by summing a first range-space gimbal rate required to produce a torque to an overall gimbal rate achieve a desired maneuver of the spacecraft and a first null-space gimbal rate required to maximize the ability to provide torque in a given direction; computing a singularity avoiding gimbal rate by summing a second range-space gimbal rate required to produce a torque to achieve a desired maneuver of the spacecraft and a second null-space gimbal rate required to assist in the avoidance of singularities; and determining an overall gimbal rate from an optimized combination of the momentum maximizing gimbal rate and the singularity avoiding gimbal rate. Claim: 12. The method of claim 11 wherein computing an overall gimbal rate further comprises computing a null-space gimbal rate based on the projection of a gimbal rate that produces a momentum vector perpendicular to the current direction of the torque onto the null space of an array Jacobian. Claim: 13. The method of claim 11 wherein computing a second null-space gimbal rate further comprises computing a null-space gimbal rate based on the projection of the determinant of the product of a Jacobian matrix and the transpose of an array Jacobian. Claim: 14. The method of claim 11 wherein computing a second null-space gimbal rate further comprises computing a null-space gimbal rate based on the projection of the eigenvalues of the product of a Jacobian matrix and the transpose of an array Jacobian. Current U.S. Class: 244165/000 Current International Class: 64

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METHOD AND SYSTEM FOR OPTIMIZING TORQUE IN A CMG ARRAY