Spacecraft gyro calibration system
November 26, 2023. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.Patent References 3242744 Side slip angle command SCAS for aircraft Integrated-strapdown-air-data sensor system Active damping of satellite nutation Unified spacecraft attitude control system Gyroless yaw control system for a three axis stabilized, zero-momentum spacecraft Tracking system for tracking targets with a spacecraft Method and apparatus for four wheel steering control utilizing tire characteristics On-board three-axes attitude determination and control system Method for in-field updating of the gyro thermal calibration of an intertial navigation system InventorsAssigneeApplicationNo. 10723782 filed on 11/26/2003US Classes:244/171, With attitude sensor means74/5.34, Multiple gyroscopes244/179, By change in bank701/220, Using inertial sensor244/170, By nutation damper701/226, Space orbits or paths244/165, By gyroscope or flywheel342/95, Automatic range tracking701/42, Feedback, transfer function or proportional and derivative (P& D) control244/164, Attitude control244/195, Self-adaptive control702/95, Coordinate positioning702/151, Angular position73/1.78, Aircraft, inertial navigation, or attitude73/178R, NAVIGATION701/13, Spacecraft or satellite701/4, Altitude or attitude control or indication33/328, Attitude indicator (i.e., pitch or bank)244/3.16Optical (includes infrared)ExaminersPrimary: Carone, Michael J.Assistant: Holzen, Stephen A Attorney, Agent or FirmInternational ClassesG01C 17/38G06F 15/00 AbstractA method of calibrating a gyro (42) of a spacecraft (14) may include determining a yaw attitude residual of the spacecraft. Roll gyro bias residual is determined in response to the yaw attitude residual. The gyro (42) is calibrated in response to the roll gyro bias residual. A method of calibrating a gyro (42) of a spacecraft (14) may alternatively include disabling gyro calibration, gain scheduling, or resetting attitude and gyro bias covariance, for selective axes, for a yaw transient period. The gyro (42) is calibrated in a nominal fashion after completion of the yaw transient period.Other References
Field of SearchSPACECRAFTSpacecraft formation, orbit, or interplanetary path Orbit insertion Orbital control Attitude control With attitude sensor means Yaw control Submarine and torpedo systems Landing systems Altitude or pitch control Multiple mode systems Marine vehicles Roll control Celestial navigation Radio-controlled Vehicular guidance systems with single axis control Land vehicles | |
