Recursive satellite attitude estimation with the two-step optimal estimator

N. Jeremy Kasdin, Thomas J.M. Weaver

Research output: Chapter in Book/Report/Conference proceedingConference contribution

7 Scopus citations

Abstract

This paper presents a new approach to recursive satellite attitude determination from vector observations that utilizes the two-step optimal estimator. It will be shown that near optimal results are obtained with very realistic noise and sensor models. The twostep estimator was introduced in 1995 as an alternative to the Extended Kalman Filter (EKF) for recursive estimation with nonlinear measurements. By breaking the measurement update process into two-steps, a linear first step using a nonlinear transformation of the desired states and a non-recursive second step minimization to recover the desired states, a near optimal estimation is possible. It has been shown that for certain systems this process recovers the global optimal solution. It will be demonstrated here that the problem of estimating the quaternion attitude representation of a satellite comes very close to this global optimum. Simulations will show dramatic improvements in performance over the traditional EKF and other attitude estimators.

Original languageEnglish (US)
Title of host publicationAIAA Guidance, Navigation, and Control Conference and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624101083
StatePublished - Jan 1 2002
EventAIAA Guidance, Navigation, and Control Conference and Exhibit 2002 - Monterey, CA, United States
Duration: Aug 5 2002Aug 8 2002

Publication series

NameAIAA Guidance, Navigation, and Control Conference and Exhibit

Other

OtherAIAA Guidance, Navigation, and Control Conference and Exhibit 2002
CountryUnited States
CityMonterey, CA
Period8/5/028/8/02

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

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    Kasdin, N. J., & Weaver, T. J. M. (2002). Recursive satellite attitude estimation with the two-step optimal estimator. In AIAA Guidance, Navigation, and Control Conference and Exhibit (AIAA Guidance, Navigation, and Control Conference and Exhibit). American Institute of Aeronautics and Astronautics Inc..