Common Modular Integrated Shell/Surface Interface for Tensionless Reflective RF Surface Apertures

The proposed PII capitalizes on the positive PI results that established the feasibility of a modular, common, integral, shell/structure interface for segmented, tensionless, reflective RF apertures. The resulting common-interface mounting system concept has been intentionally designed so that Mevicon’s Membrane Aperture Shells can be mounted on a wide range of potential current and future support-structure architectures. Activity will focus on the critical path interface items of innovative shell mounting, roll-stowage compliance mechanisms, launch-constraint methods that are critical to realizing the promise of the very low areal density (70 to 180 g/m2), compact roll-stowage, and self-deployment that are key features of Mevicon’s RF proven Membrane Aperture Shell Technology. Development work is focused on the ORS Common Aperture requirements, but the resulting technology will be applicable to a broader range of aperture applications and structure approaches. Building on PI successes, we will, together with our PII industry transition teammates, continue to advance shell/structure interface solutions, perform detailed design and component studies, develop demonstrators and “readiness for flight” testbeds, and develop a flight design, thereby improving TRL levels. This will prepare the way for a space flight demonstration, which is a key step in any realistic commercialization plan for space hardware. BENEFIT: The potential pay-off of the proposed research can be summarized at the highest level as “Less Mass, More Responsive,” reflective, doubly-curved RF apertures. The proposed technology is a cross cutting one and is directly applicable to the needs of the ORS for a Common RF Aperture Solution, as well as to many of the AF technical areas (RS, SSA, CCC, DCS, ISR) as the reflective apertures can be used for host satellite functions (typically RF communication), as well as on the payload side (signal or image collection). The basic advantage is that both more-affordable apertures for the same size and larger apertures for the same mass have positive cascading impacts throughout the satellite design, enabling either on launch vehicle more mission from a given bus or the use of smaller bus components. While the end goal is to development a segmented RF reflector aperture approach capable of meeting the ORS Common Aperture requirements, this Phase II is focused on developing an innovative, modular, segment/structure interface solution for dual-roll-stowed shells that can support a range of support structure concepts. This maximizes the commercialization transition path opportunities. Once developed and flight demonstrated, this will open additional opportunities for government satellite applications, as well as commercial space applications, particularly in the areas of space-based RF communications and space science. There are possible applications as solar concentrators for potential use in solar dynamic power generation and future space orbital propulsion (solar thermal propulsion). Terrestrially, applications are foreseen in transportable emergency apertures for commercial telecom, back-packable solar concentrators for water heating, cooking, and distillation.