A study is reported on attitude measurement systems using outputs of optical and inertial sensors combined to provide a high quality attitude reference of spacecraft or inertial platforms, undergoing both small attitude precision motion (pointing mode), and a large angle sleeving motion. The systems considered use a star tracker capable of tracking two stars, and inertial quality rate integrating gyros. Processing is carried out digitally using a processor based on the Adaptive Control Electronics (ACE) computer. The determination of the attitude, expressed in times of modified Euler angles, using filtering techniques is described. These factors are derived using Wiener theory, and they optimally mix the star tracker and gyro outputs. Application of the preferred form of attitude measurement is considered for a specific satellite mission.
Study of Strapdown Inertial Optical Attitude Measurement Systems, Volume 2
1977
268 pages
Report
Keine Angabe
Englisch
Strapdown inertial attitude-indication evaluations
AIAA | 1970
|Strapdown inertial attitude-indication evaluations
NTRS | 1970
|Strapdown inertial attitude-indication evaluations
NTRS | 1970
|