This 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.
Spacecraft Angular State Estimation After Sensor Failure
Intelligent Systems and Control (ISC 2002) ; 2002 ; Tsukuba, Japan
01.10.2002
Aufsatz (Konferenz)
Keine Angabe
Englisch
Spacecraft Angular State Estimation after Sensor Failure
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