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).

Abstract: According to the present invention, a battery cell sleeve assembly includes a continuous tubular sleeve extending between proximal and distal ends and has a plurality of substantially unidirectional longitudinally extending elongated heat conduction fibers having a thermal conductivity no less than that of aluminum embedded in a suitable matrix. The sleeve is received on the outer peripheral surface of a tubular battery cell which is typically, but not necessarily cylindrical and in a contiguous relationship with the battery cell. A tubular base member having a peripheral flange is attached to the continuous tubular sleeve such that the distal ends of the heat conduction fibers are contiguous with the peripheral flange. With this construction, the peripheral flange operates as a heat shunt for drawing heat away from the continuous tubular sleeve by conduction between the heat conduction fibers and the peripheral flange.