In this paper, piezoelectric feedback control of vibration and instability of spacecraft booms modeled as circular thin-walled cross-section beams and subjected to solar radiant heating is investigated. Having in view that composite material systems are likely to play a great role in the design of these devices, the beam constituent materials encompass non-classical effects such as anisotropy and transverse shear. In addition, in order to induce beneficial elastic couplings, a special ply-angle distribution achieved via the usual helically wounding fiber-reinforced technology, the so called filament winding, is implemented. The dynamic governing equations including the temperature effects and the related boundary conditions are obtained via the application of Hamilton's principle. Toward the end of controlling the oscillations and prevent the occurrence of the thermal dynamic instability, a feedback control capability based on the use of the piezoelectric induced strain actuation is implemented. The performance of its implementation considered in conjunction with that of the structural tailoring are highlighted and pertinent conclusions are derived.
Vibration control of composite spacecraft booms subjected to solar heating
Schwingungsregelung von Raumfahrzeugauslegern aus Verbundwerkstoff bei solarer Erwärmung
Journal of Thermal Stresses ; 32 , 1-2 ; 95-111
2009
17 Seiten, 7 Quellen
Article (Journal)
English
Raumfahrzeug , Steuerung und Regelung , Ausleger , Sonnenstrahlung , Scherbeanspruchung , elastisches Verbindungselement , Wickelverbundwerkstoff , Wickelformen , Hamilton-Theorie , mathematische Gleichung , piezoelektrischer Aktor , Schwingungsbegrenzung , faserverstärkter Verbundwerkstoff , Schwingungssteuerung und -regelung
Thermally Induced Bending Vibration of Composite Spacecraft Booms Subjected to Solar Heating
British Library Conference Proceedings | 2002
|British Library Conference Proceedings | 2004
|NTRS | 1970
|