Highlights Viscoelastic properties of candidate polymers for deployable composite boom. The prediction of relaxation in modulus of polymers in 1 and 2 year at room temperature. The effect of free volume on the molecular rearrangement and relaxation. The effect of carbon fiber on the viscoelastic properties of composite.
Abstract Deployable space structures are being built from thin-walled fiber-reinforced polymer composite materials due to their high specific strength, high specific stiffness, and designed bistability. However, the inherent viscoelastic behavior of the resin matrix can cause dimensional instability when the composite is stored under strain. The extended time of stowage between assembly and deployment in space can result in performance degradation and in the worst case, mission failure. In this study, the viscoelastic properties of candidate commercial polymers consisting of difunctional and tetrafunctional epoxies and thermoplastic and thermosetting polyimides were evaluated for deployable boom structures of solar sails. Stress relaxation master curves of the candidate polymers were used to predict the relaxation that would occur in 1 year at room temperature under relatively low strains of about 0.1%. A bismaleimide (BMI) showed less stress relaxation (about 20%) than the baseline novolac epoxy (about 50%). Carbon fiber composites fabricated with the BMI resin showed a 44% improvement in resistance to relaxation compared to the baseline epoxy composite.
Viscoelastic characterization of polymers for deployable composite booms
Advances in Space Research ; 67 , 9 ; 2727-2735
2020-07-25
9 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
British Library Conference Proceedings | 2003
|Design of Ultrathin Composite Self-Deployable Booms
AIAA | 2014
|Low-Mass Deployable Spacecraft Booms
British Library Conference Proceedings | 2010
|