Spacecraft Angular State Estimation After Sensor Failure

I.Y. Bar-Itzhack (Israel) and R.R. Harman (USA)

Keywords

Attitude Determination, Angular Rate Computation, Kalman Filtering, Sensor Failure.

Abstract

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.

Important Links:

• DOI:
• From Proceeding (366) Intelligent Systems and Control - 2002

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