The attitude specified in terms of the three Eulerian angles, is related to the angular velocity components in body-fixed co-ordinates by three coupled first-order non-linear differential equations. This study presents a new analytical approach to these equations by first reducing the problem to a single second-order non-linear differential equation and then establishing its equivalence with a second-order 2linear1 differential equation for a satellite spinning with constant angular velocity components. The solution of this equivalent linear equation is then used to obtain the Eulerian angles.
An analytical approach to attitude determination of a spinning satellite
Ein analytisches Verfahren zur Bestimmung der Fluglage eines sich drehenden Satelliten
Aeronautical Journal ; 78 , 762 ; 256-257
1974
, 2 Quellen
Article (Journal)
English
Attitude determination for a spinning satellite
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|Magnetic attitude control of spinning satellite
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