The method of linear covariance analysis is applied to the study of an aerospace vehicle integrated guidance-and-navigation system. This requires that the rms trajectory deviations of the vehicle be computed along with the rms errors of the navigation system. The technique is used to examine the performance of the shuttle orbiter vehicle's guidance-and-navigation system during the terminal phase of the landing. Essentially the same rms trajectory deviations were obtained from a single covariance run as from a 30-sample Monte-Carlo run set. Of particular interest in the study was the result that rms trajectory deviations for the integrated-system were generally significantly larger than the rms navigation errors.
Performance evaluation of integrated guidance and navigation systems
NAECON ''78; National Aerospace and Electronics Conference ; 1978 ; Dayton, OH
01.01.1978
Sonstige
Keine Angabe
Englisch
Integrated navigation and guidance systems
TIBKAT | 1999
|Integrated navigation and guidance systems
SLUB | 1999
|