On-orbit gyro calibration for operationally responsive space systems

Richard Linares, John L. Crassidis, Puneet Singla

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

3 Scopus citations

Abstract

This paper presents a method for accurate on-orbit calibration of rate-integrating threeaxis gyroscopes. On-orbit calibration is required for operationally responsive space systems in order to deal with rapidly changing technology and support needs. However, a tradeoff usually occurs between accuracy and speed of convergence of the to-be-determined calibration parameters. In order to achieve a fully autonomous and accurate calibration approach, a two-step process is proposed. The first step determines an initial estimate of the gyro calibration parameters using an angular velocity estimate determined from a star tracker. This angular velocity estimate is provided without the need to identify stars, thereby bypassing the associated adverse issues that typically arise in star tracker attitude determination systems. The second step uses the initial gyro calibration estimates in a generalized multiple-model adaptive estimation approach, which combines outputs from three filters to determine estimates that are better than each filter alone. Simulation results are shown to assess the performance of the proposed on-orbit calibration approach.

Original languageEnglish (US)
Title of host publicationAIAA/AAS Astrodynamics Specialist Conference 2010
DOIs
StatePublished - 2010
EventAIAA/AAS Astrodynamics Specialist Conference 2010 - Toronto, ON, Canada
Duration: Aug 2 2010Aug 5 2010

Publication series

NameAIAA/AAS Astrodynamics Specialist Conference 2010

Other

OtherAIAA/AAS Astrodynamics Specialist Conference 2010
CountryCanada
CityToronto, ON
Period8/2/108/5/10

Bibliographical note

Funding Information:
This work was sponsored by the Air Force Research Laboratory’s Space Vehicles Directorate grant number FA9453-09-C-0356 under the supervision of Captain Chester Douglas McFarland. The authors greatly appreciate the support. The authors also wish to thank Dr. Quang Lam from Orbital Sciences Corporation for many help discussions and comments.

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