Abstract: A cryogenic propellant depot and sunshield are provided for operation in earth orbit to fuel or refuel other space vehicles. The sunshield is deployed to effectively mitigate solar radiation emanating from the earth and the sun thereby providing a long term storage solution for cryogenic fluids prone to boil-off. The depot has supporting subsystems to include station keeping equipment and communication equipment so that the depot can be independently controlled. Inflatable booms are used to deploy the sunshield in a desired pattern around the depot.

Abstract: A cryogenic propellant depot and sunshield are provided for operation in earth orbit to fuel or refuel other space vehicles. The sunshield is deployed to effectively mitigate solar radiation emanating from the earth and the sun thereby providing a long term storage solution for cryogenic fluids prone to boil-off. The depot has supporting subsystems to include station keeping equipment and communication equipment so that the depot can be independently controlled. Inflatable booms are used to deploy the sunshield in a desired pattern around the depot.

Abstract: A cryogenic propellant depot and sunshield are provided for operation in earth orbit to fuel or refuel other space vehicles. The sunshield is deployed to effectively mitigate solar radiation emanating from the earth and the sun thereby providing a long term storage solution for cryogenic fluids prone to boil-off. The depot has supporting subsystems to include station keeping equipment and communication equipment so that the depot can be independently controlled. Inflatable booms are used to deploy the sunshield in a desired pattern around the depot.

Abstract: An inflatable antenna system combining a fixed aperture with an inflatable aperture that greatly increases the reflector size of the antenna system. The fixed portion provides a “risk buffer” in that a moderate gain capability is retained in the event of an inflation failure. In a parabolic dish embodiment, an inflatable annulus is stowed compactly under a fixed dish to fit a variety of spacecraft and launch vehicle envelopes. Moderate gas pressure deploys the inflatable portion, which forms a larger reflector surface. After inflation, the materials that form the inflated reflector surface can be made rigid. A fixed feed system for the smaller fixed dish assures operation of the smaller fixed dish throughout the mission. Moreover, the smaller fixed antenna can receive signals that can be used to derive pointing information used to point the larger inflated antenna in a particular direction thus providing a dual-use capability.