Abstract: A hybrid image gathering and data transmission system is provided. The system includes at least one parabolic reflector to gather, disseminate and direct electromagnetic radiation. A beam splitter using a Fresnel zone plate (FZP) is configured and arranged to receive and/or transmit the electromagnetic radiation from or to the at least one parabolic reflector and separately focus microwave radiation and visual radiation. The beam splitter provides a gain in the microwave radiation and the visual radiation. A radio frequency (RF) receiver/transmitter receives and transmits the microwave radiation from or to the beam splitter and a focal plane array (FPA) receives the visible radiation from the beam splitter. A processor is in communication with the RF receiver and the FPA. The processor processes signals received by the RF receiver and the FPA and provides processed data to be transmitted to a remote location.

Abstract: Payload adapters for launch vehicles include a ring structure having an opening formed therein and at least a portion of an antenna assembly coupled to a circular sidewall of the ring structure at least partially within the opening of the ring structure. Satellite assemblies may include a payload adapter comprising a ring structure having a circular opening formed therein and an antenna assembly including a parabolic reflective dish formed within the circular opening. Launch stack systems may include a primary payload and a secondary payload adapter including an antenna dish integrally formed with a ring structure of the secondary payload adapter. Methods of forming a satellite assembly include positioning at least a portion of the antenna assembly within an opening formed in a ring-shaped payload adapter for a launch vehicle and coupling the at least a portion of the antenna assembly to the ring-shaped payload adapter.

Abstract: A system and method for deploying a satellite having an integrated bus and an aperture, wherein the integrated bus extends along its longitudinal axis and wherein the aperture intersects the longitudinal axis. The satellite is deployed into an orbit, wherein deploying includes orienting the satellite so that the aperture points at a desired location. The satellite is spun so that the logitudinal axis and the aperture remain pointing at the desired location and data regarding the desired location is captured via the aperture.

Abstract: Payload adapters for launch vehicles include a ring structure having an opening formed therein and at least a portion of an antenna assembly coupled to a circular sidewall of the ring structure at least partially within the opening of the ring structure. Satellite assemblies may include a payload adapter comprising a ring structure having a circular opening formed therein and an antenna assembly including a parabolic reflective dish formed within the circular opening. Launch stack systems may include a primary payload and a secondary payload adapter including an antenna dish integrally formed with a ring structure of the secondary payload adapter. Methods of forming a satellite assembly include positioning at least a portion of the antenna assembly within an opening formed in a ring-shaped payload adapter for a launch vehicle and coupling the at least a portion of the antenna assembly to the ring-shaped payload adapter.

Abstract: A modular payload carrier for use in a launch vehicle includes at least one module configured to fit in a payload bay of the vehicle and attachable to at least one other module configured to fit in the bay. The module includes an outer wall contoured generally to fit a bottom surface contour of the bay. The carrier can be used for the manifesting of both deployable and non-deployable payloads. Processing of payloads with the carrier can be performed, in large part, separately from launch vehicle processing. Thus launch costs and turnaround times can be reduced.

Abstract: A modular payload carrier for use in a launch vehicle includes at least one module configured to fit in a payload bay of the vehicle and attachable to at least one other module configured to fit in the bay. The module includes an outer wall contoured generally to fit a bottom surface contour of the bay. The carrier can be used for the manifesting of both deployable and non-deployable payloads. Processing of payloads with the carrier can be performed, in large part, separately from launch vehicle processing. Thus launch costs and turnaround times can be reduced.

Abstract: A Stirling engine heater head is constructed to provide an annular heat exchange region defined between a pressure vessel sidewall and the engine displacer cylinder. From an external manifold, through which a heated fluid flows, either heat pipes or heat exchange tubes are sealingly introduced into the heat exchange region. Thermal energy is thus transferred to the engine working fluid, while the heated fluid is maintained isolated from the vessel walls and the displacer cylinder. For a compound Stirling engine configuration, thermal energy is introduced from a common heated fluid manifold to the heat exchange regions of a pair of axially aligned Stirling engine modules via heat pipes or heat exchange tubes. This manifold may be sealingly joined with the pressure vessel to create a chamber which is pressurized to pressure balance the vessel walls.

Abstract: A power conversion system is constructed of a plurality of identical Stirling engine modules paired off in opposed, aligned relation with their respective expansion spaces in juxtaposition. Two engine module pairs are arranged in a common plane and in mutually perpendicular relation to create a module group, with plural such module groups stacked together to provide an expanded, self-balanced system with all the modules sharing a common, centrally located thermal energy source. Each module includes a pair of compression positions operating on a common axis intersecting the displacer cylinder axis at right angles. Heat exchangers, either tubes or heat pipes, are disposed within the expansion space to transfer heat from the source to the working fluid therein, thus providing a more idealized Stirling engine cycle.