Abstract: A space vehicle including a reflective component on the side thereof for reflecting electromagnetic radiation, such as a mirror, the composite being formed by the steps of providing a composite support structure; providing a release liner including a metallic layer having a thickness between 1 and 5 microns on a surface thereof; situating the release liner against the surface of the composite support structure so that the metallic layer of the release liner is placed in direct, physical contact with the surface of the support structure; removing the release liner so that the metallic layer remains attached to the surface of the support structure; and mounting the support structure on a support on the exterior of the space vehicle.

Abstract: A method of metallizing a surface of a structure, and in some embodiments a mirror produced by such method, by the steps of providing a composite support structure; providing a release liner including a metallic layer having a thickness between 1 and 5 microns on a surface thereof; situating the release liner against the surface of the composite support structure so that the metallic layer of the release liner is placed in direct, physical contact with the surface of the support structure; and removing the release liner so that the metallic layer remains attached to the surface of the support structure.

Abstract: A retractable and re-deployable assembly is provided for collecting electromagnetic energy, for instance in outer space. The assembly has two layers: a first layer comprising a substrate and a second layer comprising an array of electromagnetic transducers. The second layer may further include a plurality of panels, each of which has a proximal edge and a distal edge opposite to the proximal edge. The panels also have a reflective surface and opposite the reflective surface a collector surface on which the array of electromagnetic transducers is disposed. The panels may be flexible and pre-formed to a cylindrical parabolic shape such that when this embodiment is in the deployed configuration, the edge of the panel curls away from the substrate layer because of the pre-formed parabolic shape, thus helping focus the energy on the transducers.

Abstract: A retractable and re-deployable boom assembly is provided for collecting electromagnetic energy, for instance in outer space. The assembly may include a boom having a deployable length and a first layer comprising a flexible substrate formed in a lenticular shape that elastically deforms, and a second layer thereon comprising an array of electromagnetic transducers, which may be positioned on adjacent flexible parabolic reflectors. The assembly may be placed into at least two different configurations: a stowed configuration where the majority of the length is elastically deformed; and a deployed configuration where the majority of the length is not deformed, and where the lenticular shape of the boom provides it with rigidity. The assembly may also have a rotational drive mechanism.