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Nonlinear Observability Analysis of Spacecraft Attitude and Angular Rate with Inertia Uncertainty

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Abstract

The observability of spacecraft attitude and angular rate is analyzed using notions from nonlinear systems theory. Exploiting the distinctive structure of the system, expressions for its Lie derivatives of any order are derived. The observability mapping is then constructed and analyzed, yielding that the system is nonuniformly observable. Necessary and sufficient conditions for the system to become unobservable are derived. It is further shown that the angular rate unobservability conditions, thus derived, are a generalization of previously obtained results. Additionally, the observability of the inertia tensor is examined, and it is shown that the inertia is nonuniformly observable. A sufficient condition is given under which the control input (generated, e.g., by the momentum wheel) renders the inertia unobservable. This phenomenon is numerically demonstrated using a Bayesian grid-based filter that is applied to the estimation of the attitude and angular rate of a spacecraft subjected to inertia tensor uncertainty.

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Authors and Affiliations

  1. Department of Aerospace Engineering, Technion — Israel Institute of Technology, Haifa, 32000, Israel

    Avishy Carmi (Doctoral Student) & Yaakov Oshman (Professor, Holder of the Louis and Helen Rogow Chair in Aeronautical Engineering)

Authors
  1. Avishy Carmi
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  2. Yaakov Oshman
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Corresponding author

Correspondence to Avishy Carmi.

Additional information

Presented at the F. Landis Markley Astronautics Symposium, Cambridge, Maryland, June 29–July 2, 2008.

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Carmi, A., Oshman, Y. Nonlinear Observability Analysis of Spacecraft Attitude and Angular Rate with Inertia Uncertainty. J of Astronaut Sci 57, 129–148 (2009). https://doi.org/10.1007/BF03321498

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