An analytical approach is presented for the stick-slip of the TCM (Tension Control Mechanism) by means of spacecraft attitude responses. The mathematical model utilized assumes that the spacecraft was composed of a main rigid body and flexible appendages, which consist of a number of rigid plates connected by torsional hinges. Key parameters of the hinges are determined by applying the equations of the vibration of a uniform cantilever beam with tangible physical parameters. This mathematical model was evaluated using the ADEOS (ADvanced Earth Observing Satellite) and ADEOS-II flight data and ground-based test data. It is concluded that the technical approach and mathematical model utilized have correctly represented actual spacecraft motions.
Dynamic simulation of stick-slip motion of a flexible solar array
Dynamische Simulation der Stick-Slip-Bewegung einer flexiblen Solaranlage
Control Engineering Practice ; 16 , 6 ; 724-735
2008
12 Seiten
Article (Journal)
English
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