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Spacecraft methods and structures with enhanced attitude control that facilitates gyroscope substitutions
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 2004 |
| Description | Methods and structures are provided that enhance attitude control during gyroscope substitutions by insuring that a spacecraft's attitude control system does not drive its absolute-attitude sensors out of their capture ranges. In a method embodiment, an operational process-noise covariance Q of a Kalman filter is temporarily replaced with a substantially greater interim process-noise covariance Q. This replacement increases the weight given to the most recent attitude measurements and hastens the reduction of attitude errors and gyroscope bias errors. The error effect of the substituted gyroscopes is reduced and the absolute-attitude sensors are not driven out of their capture range. In another method embodiment, this replacement is preceded by the temporary replacement of an operational measurement-noise variance R with a substantially larger interim measurement-noise variance R to reduce transients during the gyroscope substitutions. |
| File Size | 867862 |
| Page Count | 13 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20080007445 |
| Archival Resource Key | ark:/13960/t0fv3hz86 |
| Language | English |
| Publisher Date | 2004-01-20 |
| Access Restriction | Open |
| Subject Keyword | Astrodynamics Patents Gyroscopes Attitude Control Attitude Indicators Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Patent |
