Stability Analysis for Constrained Principal Axis Slew Maneuvers

This paper addresses the problem of reorienting a rigid spacecraft from arbitrary initial conditions to prescribed final conditions with zero angular velocity. The control law analyzed is based on quaternion feedback and leaves the user to choose two gains as functions of position, angular rate, and...

Ausführliche Beschreibung

Bibliographische Detailangaben

Hauptverfasser:	Seywald, Hans, Lim, Kyong B., Anthony, Tobin C.
Format:	Report
Sprache:	eng
Schlagworte:	Aircraft Stability And Control
Online-Zugang:	Volltext bestellen
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