A relationship is derived for the drift of a coordinate transformation matrix of a quantized (pulsed) attitude reference system on a vehicle undergoing a “coning motion”. Several sources of limit cycle oscillations in missiles and spacecraft are studied to determine the nature of such coning motions. Typical transformation drifts are computed for these system effects.
The Drift of a Quantized Attitude System Due to Vehicle Coning Motions
Sae Technical Papers
NASA Aerospace Vehicle Flight Control Conference ; 1965
01.02.1965
Aufsatz (Konferenz)
Englisch
Drift of quantized attitude system due to vehicle coning motions
Engineering Index Backfile | 1965
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