Authors
Abstract
This paper presents an improved deployable reflector concept for an Earth
observation mission that requires a low-cost L-band Synthetic Aperture Radar
(SAR) satellite. The required reflector shape is an offset parabolic cylinder with an
arc length of 7.888 m and a width of 3.2 m. A novel hollow solid structural
concept is proposed that comprises curved surfaces formed from thin sheets of
carbon-fiber-reinforced-plastic (CFRP) connected by flexible hinges along the
edges. This proposed structure has very high stiffness-to-weight-ratio, because of
its thin-walled box-type construction. A preliminary design of the full-scale
structure in deployed configuration, which has an estimated mass 22.5 kg and
18.665 kg and fundamental natural frequency of 0.72 Hz and 0.64 Hz before and
after the optimization analysis respectively, is presented in the paper. This is 3.5 to
4.2 times lighter than the traditional reflector structure, made from lightweight
curved panels with self-locking hinges. A detailed study of a quarter-scale
technology demonstrator made of 0.6mm thick thermoplastic (nylon), including
design, manufacture and testing is also presented.
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