Strain energy deployable composite structures offer spacecraft designs reduced payload and compact volume. One of the greatest advantages presented by deployable composite structures arises from their ability to maintain high-strain configurations for extended periods of stowage. Because of the viscoelastic nature of the polymer matrix, the stowed composite structure undergoes stress relaxation that results in a decrease of the energy available for deployment. This paper focuses on a three-layered ( ± 45    deg plain weave / 0    deg unidirectional / ± 45    deg plain weave ) carbon-fiber-reinforced polymer composite deployable structure, known as a tape spring. Stress relaxation testing was used to define the viscoelastic behavior of the epoxy matrix. Experimental long-term stowage and deployment testing was performed on the ( ± 45 / 0 / ± 45    deg ) tape spring specimens. Finite element simulations considering viscoelastic, orthotropic stress relaxation were developed to predict the effects of stress relaxation on the deployment of a ( ± 45 / 0 / ± 45    deg ) tape spring.


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    Titel :

    Stowage and Deployment of a Viscoelastic Orthotropic Carbon-Fiber Composite Tape Spring


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2018-06-27


    Format / Umfang :

    12 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch