This paper presents an attitude acquisition sequence which minimizes the use of sensors, logic, and propellant. The technique is based upon an open-loop maneuver using the torque motor to simultaneously reorient the satellite and spin up the wheel. A physical interpretation of this dynamic sequence is of primary concern because this maneuver has not been well understood, nor have practical quantitative performance equations or stability conditions for the spacecraft designer been forthcoming. Results indicate that this maneuver is practical only when the initial spin axis is the axis of maximum inertia. Otherwise, it results in unstable motion or very large values of nutation angle with respect to the wheel axis. A simple nutational performance equation is also presented.
Attitude acquisition maneuver for bias momentum satellites
Fluglagenregelung bei Satelliten
Comsat Technical Review ; 6 , 1 ; 1-24
1976
24 Seiten, 8 Quellen
Aufsatz (Zeitschrift)
Englisch
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