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Four methods of attitude determination for spin-stabilized spacecraft with applications and comparative resultsThe attitude of a spacecraft is determined by specifying independent parameters which relate the spacecraft axes to an inertial coordinate system. Sensors which measure angles between spin axis and other vectors directed to objects or fields external to the spacecraft are discussed. For the spin-stabilized spacecraft considered, the spin axis is constant over at least an orbit, but separate solutions based on sensor angle measurements are different due to propagation of errors. Sensor-angle solution methods are described which minimize the propagated errors by making use of least squares techniques over many sensor angle measurements and by solving explicitly (in closed form) for the spin axis coordinates. These methods are compared with star observation solutions to determine if satisfactory accuracy is obtained by each method.
Document ID
19750022162
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Report (TR)
Authors
Smith, G. A. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1975
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
G-7522
NASA-TR-R-445
Accession Number
75N30235
Funding Number(s)
PROJECT: RTOP 311-07-14-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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