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In-flight calibration of the fine pointing Sun sensor on the solar maximum missionThe attitude control objectives of solar maximum mission are to point the boresight of the payload fine pointing sun sensor (FPSS) to any point within 30 arc-minutes of the Sun's center with an accuracy of 5 arc-seconds (3 sigma, pitch and yaw) and a jitter of less than 3 arc-seconds (3 sigma). To meet these stringent accuracy requirements, a procedure was developed for in-flight calibration of the FPSS. The spacecraft was maneuvered using FPSS offset commands to position the Sun at different points within the FPSS field of view. The coefficients of the FPSS digital to analog nonlinear transfer function were determined by minimizing the residuals between the pitch and yaw angles computed from the FPSS measurements and the corresponding reference angles obtained from inertial reference unit measurements. The actual in-flight calibration and the calibration algorithm are discussed.
Document ID
19810002577
Document Type
Conference Paper
Authors
Gambardella, P. J. (Computer Sciences Corp. Silver Spring, MD, United States)
Thompson, R. H. (Computer Sciences Corp. Silver Spring, MD, United States)
Date Acquired
August 11, 2013
Publication Date
October 1, 1980
Publication Information
Publication: NASA. Goddard Space Flight Center Fifth Ann. Flight Mech.(Estimation Theory Symp.
Subject Category
ASTRODYNAMICS
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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Related Records

IDRelationTitle19810002562Analytic PrimaryFifth Annual Flight Mechanics/Estimation Theory Symposium