Abstract: A lighting device having a power failure mode for use with one or more other networked devices is disclosed. In embodiments, the lighting device may comprise an outer globe, a diffuser, a plurality of light pipes, an outer cowling, a power input connector, a power control printed circuit board, a communication and control printed circuit board, an indicator printed circuit board, one or more microprocessors, an auxiliary device, and an LED lighting printed circuit board. In embodiments, the lighting device may communicate with one or more other networked devices, such as second lighting devices, mobile phones, servers, remote controls, and/or home or office automation equipment. The lighting device may be powered through a light socket or a backup battery in a power failure mode.

Abstract: A lighting device for use with one or more other networked devices is disclosed. In embodiments, the lighting device may comprise an outer globe, a diffuser, an outer cowling, a power input connector, a power control printed circuit board, a communication and control printed circuit board, an indicator printed circuit board, one or more microprocessors, a real-time clock, a supercapacitor, and an LED lighting printed circuit board. In embodiments, the real-time clock may be powered by the supercapacitor to track time without power from an input power source for the lighting device, enabling the lighting device to implement time-dependent settings, such as pre-programmed color temperatures and/or light intensities. The lighting device may communicate with one or more other networked devices, such as second lighting devices, mobile phones, servers, remote controls, and/or home or office automation equipment. The lighting device may be powered through a light socket.

Abstract: A lighting device for use with one or more other networked devices is disclosed. In embodiments, the lighting device may comprise an outer globe, a diffuser, a plurality of light pipes, an outer cowling, a power input connector, a power control printed circuit board, a communication and control printed circuit board, an indicator printed circuit board, one or more microprocessors, an auxiliary device, and an LED lighting printed circuit board. In embodiments, the lighting device may communicate with one or more other networked devices, such as second lighting devices, mobile phones, servers, remote controls, and/or home or office automation equipment. The lighting device may be powered through a light socket.

Abstract: A lighting device for use with one or more other networked devices is disclosed. In embodiments, the lighting device may comprise an outer globe, a diffuser, a plurality of light pipes, an outer cowling, a power input connector, a power control printed circuit board, a communication and control printed circuit board, an indicator printed circuit board, one or more microprocessors, an auxiliary device, and an LED lighting printed circuit board. In embodiments, the lighting device may communicate with one or more other networked devices, such as second lighting devices, mobile phones, servers, remote controls, and/or home or office automation equipment. The lighting device may be powered through a light socket.

Abstract: An orbit-transfer vehicle provides the navigation, propulsion, and control systems required to transport a payload satellite from a geosynchronous-transfer orbit (GTO) to a predetermined low-earth orbit (LEO). Upon entering low-earth orbit, the payload satellite is deployed from the orbit-transfer vehicle. To reduce the cost and complexity of the payload satellite, the orbit-transfer vehicle is configured to provide common functional services, such as communications and power regulation, to the payload satellite during the transport, and/or after deployment. To reduce the fuel requirements for this deployment via the orbit-transfer vehicle, a preferred embodiment includes aerobraking to bring the satellite into a low-earth orbit.

Abstract: The excess space and weight capacity of a conventional geosynchronous-transfer launch vehicle is used to deploy satellites to a low-earth orbit (LEO). In a preferred embodiment, an orbit-transfer vehicle provides the navigation, propulsion, and control systems required to transport a payload satellite from a geosynchronous-transfer orbit (GTO) to a predetermined low-earth orbit. Upon entering low-earth orbit, the payload satellite is released from the orbit-transfer vehicle. To reduce the fuel requirements for this deployment via the orbit-transfer vehicle, a preferred embodiment includes aerobraking to bring the satellite into a low-earth orbit.

Abstract: A spacecraft architecture is defined that distinguishes components and sub-systems based on both functional and physical dependencies. On one side of the interface are kernel components that are both functionally and physically independent of the vehicle configuration and functionally and physically independent of the mission-specific system. On the other side of the interface are components that depend on either the spacecraft configuration or the mission-specific system. The kernel components can be included in a variety of spacecraft, independent of the spacecraft architecture and independent of the spacecraft mission. The kernel includes a communications system for communicating with an earth station, a command and data handling processor, and a power regulation and distribution system.

Abstract: A multi-mission spacecraft bus structure is provided which has a plurality of internal thermally-isolated cells, and a plurality of external mounting surfaces. The spacecraft bus structure comprises a plurality of half frame panels, which are secured to plurality of longerons. The half-frame panels each have a pair of broad planar surfaces, a center abutting surface, a pair of end-abutting surfaces, and a pair of miter joint surfaces. Adjacent half-frame panels can either join at the center abutting surfaces, or at the edge mounting surfaces. The bus structure is further sealed at the top and at the bottom by mounting plates. External electrical equipment bays can be secured to a plurality of the external mounting surfaces. Externally mounted radiators are provided to remove excess heat from the internal cells. The radiators each face in directions distinct from each other.

Abstract: A multi-mission spacecraft bus structure is provided which has a plurality of internal thermally-isolated cells, and a plurality of external mounting surfaces The spacecraft bus structure comprises a plurality of half frame panels, which are secured to plurality of longerons. The half-frame panels each have a pair of broad planar surfaces, a center abutting surface, a pair of end-abutting surfaces, and a pair of miter joint surfaces. Adjacent half-frame panels can either join at the center abutting surfaces, or at the edge mounting surfaces The bus structure is further sealed at the top and at the bottom by mounting plates. External electrical equipment bays can be secured to a plurality of the external mounting surfaces. Externally mounted radiators are provided to remove excess heat from the internal cells. The radiators each face in directions distinct from each other.

Abstract: A dictionary-based data compression technique wherein compression occurs at a variety of levels in response to word, phrase, super-phrase (sentence), and context-sensitive recognition. A separate dictionary is used at each compression level so that word compression occurs first, followed by phrase compression, followed by other compressions. Disclosed applications built upon the compression strategy include an idiomatic-language translator and a voice-recognition control system.