Highly dimensionally stable honeycomb core and sandwich structures for spacecraft applications
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United States of America Patent
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Issued Date -
May 1, 2003
app pub date -
Oct 31, 2001
filing date -
Oct 31, 2001
priority date (Note) -
Abandoned
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Abstract
A dimensionally stable honeycomb core and sandwich structure for use in spacecraft applications. The sandwich structure comprises inner and outer faceskins that sandwiches the dimensionally stable honeycomb core. The honeycomb core comprises a fiber and polymer laminate, oriented at a predetermined optimized angle relative to a ribbon direction of the core. Fiber is selected based on strength, modulus and thermal expansion coefficient properties. The polymer is selected based on inherent adhesive properties, coefficient of thermal expansion, moisture absorption, outgassing and its ability to perform in a space environment. The volumetric fraction of fiber and resin and the fiber angular orientation is determined based on the desired system performance, which includes achieving the lowest coefficient of thermal expansion in the plane of the sandwich (ribbon and anti ribbon), as well as through the thickness (z direction). Demanding applications may use ultra-high thermal conductivity fibers where the unidirectional thermal conductivity (K) is greater than 400 W-M/C to minimize the temperature gradients hence achieving a more uniform temperature distribution and lower distortion over the temperature range of interest.
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