Computationally efficient algorithms for real-time attitude estimationFor many practical spacecraft applications, algorithms for determining spacecraft attitude must combine inputs from diverse sensors and provide redundancy in the event of sensor failure. A Kalman filter is suitable for this task, however, it may impose a computational burden which may be avoided by sub optimal methods. A suboptimal estimator is presented which was implemented successfully on the Delta Star spacecraft which performed a 9 month SDI flight experiment in 1989. This design sought to minimize algorithm complexity to accommodate the limitations of an 8K guidance computer. The algorithm used is interpreted in the framework of Kalman filtering and a derivation is given for the computation.
Document ID
19930015520
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Pringle, Steven R. (McDonnell-Douglas Space Systems Co. Huntington Beach, CA, United States)
Date Acquired
September 6, 2013
Publication Date
February 1, 1993
Publication Information
Publication: NASA. Goddard Space Flight Center, Flight Mechanics(Estimation Theory Symposium, 1992