Precision attitude determination for multimission spacecraftAttitude determination algorithms for a multimission spacecraft are derived and their performance analyzed. The attitude determination system is composed of a strapdown Inertial Reference Unit (IRU), two fixed head star trackers, and an onboard computer. IRU data is processed to maintain real-time knowledge of spacecraft attitude relative to an inertial reference frame. Star tracker data is processed using Kalman filtering techniques to estimate and correct the attitude determination errors and the gyro drift compensation errors. The results of a star availability analysis for stellar, solar and earth pointing missions are presented. Linear covariance analysis techniques are used to evaluate nominal attitude determination performance, the effects of sensor measurement accuracy variations, the effects of errors in knowledge of sensor measurement accuracy, and the effects of star tracker misalignment errors. Results of a nonlinear simulation analysis of attitude determination performance are also presented. These analyses show that precision attitude determination for stellar, solar and earth pointing missions is achieved.
Document ID
19780066259
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Murrell, J. W. (General Electric Co., Space Div., Philadelphia Pa., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1978
Subject Category
Space Communications, Spacecraft Communications, Command And Tracking