Hub mounted bending beam for shape adjustment of springback reflectors

#1. Field of the Invention

#The present invention relates generally to spacecraft antenna reflectors and, more particularly, to a hub mounted bending beam for shape adjustment of springback reflectors.

#2. Description of the Related Art

#FIG. 1(a) is a simplified perspective view of an illustrative embodiment of a springback reflector in a manufactured configuration useful with the shape adjustment mechanism according to the present invention;

#FIG. 1(b) is a top view of the springback reflector of FIG. 1(a);

#FIG. 1(c) is a side view of the springback reflector of FIG. 1(a);

#A springback antenna reflector is provided with elastic characteristics which allow the shape of the reflector to be redefined for stowage and returned to an original shape on deployment. FIG. 1(a) is a simplified perspective diagram of an illustrative embodiment of the flexible thin-shell springback antenna reflector 10 in a manufactured configuration.

#FIG. 1(b) is a top view of the illustrative embodiment of the antenna reflector 10 in a manufactured configuration. FIG. 1(c) is a side view of the illustrative embodiment of the antenna reflector 10 in a manufactured configuration. As shown in FIGS. 1(a)-(c), in the illustrative embodiment, the reflector 10 is a parabolic shell having a coupling fixture 12 attached to the center thereof to which a support mast 14 is coupled.

#The reflector 10 is constructed of a single thin, concave homogeneous sheet of flexible, semi-rigid material such as graphite-fiber reinforced plastic. The reflector 10 may be fabricated in a conventional manner, i.e., multi-layer lamination over a precision form of the correct shape. The dimensions of the reflector 10 may be determined in a conventional manner. The reflector may be made of conductive material or nonconductive material which is coated with conductive material. A design consideration of significant importance is that the reflector 10 be sufficiently flexible to be deformed into a stowage shape and deployed to a fully non-deformed state on deployment. This requires a construction in which the deformation strain on the reflector 10 is below the creep strain limit, that is, the force at which the reflector will not return to the original shape.