NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login

Press Enter or click the Search button to begin your search.

Back to Results
Spacecraft Angular State Estimation After Sensor FailureThis work describes two algorithms for computing the angular rate and attitude in case of a gyro failure in a spacecraft (SC) with a special mission profile. The source of the problem is presented, two algorithms are suggested, an observability study is carried out, and the efficiency of the algorithms is demonstrated.
Document ID
20030020873
Acquisition Source
Goddard Space Flight Center
Document Type
Conference Paper
Authors
Bauer, Frank (NASA Goddard Space Flight Center Greenbelt, MD, United States)
BarItzhack, 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
October 1, 2002
Subject Category
Computer Programming And Software
Meeting Information
Meeting: Intelligent Systems and Control (ISC 2002)
Location: Tsukuba
Country: Japan
Start Date: October 2, 2002
End Date: October 4, 2002
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available