Abstract
Mathematical and data analysis techniques are developed to determine the attitude of a rocket whose measuring devices encounter a partial failure. These devices consist of a set of triaxial magnetometers and a lunar (solar) aspect sensor. However, for this analysis, the lunar sensor provides only the times of its measurements, not its line-of-sight angles. Magnetometer .measurements are corrected, and then used with the times of the lunar readouts and empirical lunar and magnetometer values to calculate lunar angle measurements. Standard attitude determination techniques are applied to find the elevation and azimuth of the rocket axis. Using the orientation of the rocket axis, attack angles with the lunar and magnetic field vectors are simulated. Further, if the rocket is well behaved and an orientation of its axis can be determined during this time period, then it is possible to calculate the axis of precession. These techniques are applied to rocket A09.209-1, whose primary attitude sensing devices consisted of a triaxial set of Schonstedt 600 Milligauss Magnetometers and a Bay Shore Lunar Sensor. The lunar sensor angular output was saturated for all but a few points on the lower altitude portion, but times of lunar measurements were available.
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