期刊
JOURNAL OF SPACECRAFT AND ROCKETS
卷 55, 期 4, 页码 829-840出版社
AMER INST AERONAUTICS ASTRONAUTICS
DOI: 10.2514/1.A33960
关键词
-
资金
- U.S. Air Force Office of Scientific Research [FA9550-14-1-0021]
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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