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The MAP Spacecraft Angular State Estimation After Sensor FailureThis work describes two algorithms for computing the angular rate and attitude in case of a gyro and a Star Tracker failure in the Microwave Anisotropy Probe (MAP) satellite, which was placed in the L2 parking point from where it collects data to determine the origin of the universe. The nature of the problem is described, two algorithms are suggested, an observability study is carried out and real MAP data are used to determine the merit of the algorithms. It is shown that one of the algorithms yields a good estimate of the rates but not of the attitude whereas the other algorithm yields a good estimate of the rate as well as two of the three attitude angles. The estimation of the third angle depends on the initial state estimate. There is a contradiction between this result and the outcome of the observability analysis. An explanation of this contradiction is given in the paper. Although this work treats a particular spacecraft, the conclusions have a far reaching consequence.
Document ID
Document Type
Preprint (Draft being sent to journal)
Bar-Itzhack, Itzhack Y. (Technion - Israel Inst. of Tech. Haifa, Israel)
Harman, Richard R. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2003
Subject Category
Spacecraft Instrumentation and Astrionics
Meeting Information
Israel Annual Conference on Aerospace Sciences(Tel-Aviv)
Distribution Limits
Public Use Permitted.

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NameType 20030020821.pdf STI