Abstract: An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.

Abstract: A load control system may include control devices for controlling electrical loads. The control devices may include load control devices, such as a lighting device for controlling an amount of power provided to a lighting load, and input devices, such as a remote control device configured to transmit digital messages comprising lighting control instructions for controlling the lighting load via the lighting device. The remote control device may communicate with the lighting device via an intermediary device, such as a hub device. The remote control device may detect a user interface event, such as a button press or a rotation of the remote control device. The remote control device or the hub device may determine whether to transmit digital messages to as unicast messages or multicast messages based on the type of user interface event detected.

Abstract: An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.

Abstract: A load control system may include control devices for controlling electrical loads. The control devices may include load control devices, such as a lighting device for controlling an amount of power provided to a lighting load, and input devices, such as a remote control device configured to transmit digital messages comprising lighting control instructions for controlling the lighting load via the lighting device. The remote control device may communicate with the lighting device via an intermediary device, such as a hub device. The remote control device may detect a user interface event, such as a button press or a rotation of the remote control device. The remote control device or the hub device may determine whether to transmit digital messages to as unicast messages or multicast messages based on the type of user interface event detected.

Abstract: The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

Abstract: The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

Abstract: An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.

Abstract: An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.

Abstract: A rail crossing occupancy detection system and method includes a plurality of LIDAR sensors operable to detect objects in one or more areas of interest within a field of interest, such as the areas including and surrounding a rail crossing, station, platform, or other railway right-of-way area. The field of interest is divided into one or more areas of interest, with one or more LIDAR sensors positioned to detect the presence of one or more objects within each of the one or more areas and to provide alerts based on the detection and behavior of the objects such as movement or other parameters associated with the objects.

Abstract: An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.

Abstract: A load control system may include control devices for controlling electrical loads. The control devices may include load control devices, such as a lighting device for controlling an amount of power provided to a lighting load, and controller devices, such as a remote control device configured to transmit digital messages for controlling the lighting load via the load control device. The remote control device may communicate with the lighting devices via a hub device. The remote control device may detect a user interface event, such as a button press or a rotation of the remote control device. The remote control device or the hub device may determine whether to transmit digital messages as unicast messages or multicast messages based on the type of user interface event detected. The remote control device, or other master device, may synchronize and/or toggle an on/off state of lighting devices in the load control system.

Abstract: A load control system may include control devices for controlling electrical loads. The control devices may include load control devices, such as a lighting device for controlling an amount of power provided to a lighting load, and controller devices, such as a remote control device configured to transmit digital messages for controlling the lighting load via the load control device. The remote control device may communicate with the lighting devices via a hub device. The remote control device may detect a user interface event, such as a button press or a rotation of the remote control device. The remote control device or the hub device may determine whether to transmit digital messages as unicast messages or multicast messages based on the type of user interface event detected. The remote control device, or other master device, may synchronize and/or toggle an on/off state of lighting devices in the load control system.

Abstract: The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

Abstract: An aircraft capable of vertical takeoff and landing, stationary flight and forward flight, includes a closed wing that provides lift whenever the aircraft is in forward flight, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. One or more motors are disposed within or attached to the spokes. Three or more propellers are proximate to a leading edge of the one or more spokes, distributed along the one or more spokes, and operably connected to the one or more motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight.

Abstract: A load control system may include control devices for controlling electrical loads. The control devices may include load control devices, such as a lighting device for controlling an amount of power provided to a lighting load, and input devices, such as a remote control device configured to transmit digital messages comprising lighting control instructions for controlling the lighting load via the lighting device. The remote control device may communicate with the lighting device via an intermediary device, such as a hub device. The remote control device may detect a user interface event, such as a button press or a rotation of the remote control device. The remote control device or the hub device may determine whether to transmit digital messages to as unicast messages or multicast messages based on the type of user interface event detected.

Abstract: An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.

Abstract: The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

Abstract: A load control system may include control devices for controlling electrical loads. The control devices may include load control devices, such as a lighting device for controlling an amount of power provided to a lighting load, and input devices, such as a remote control device configured to transmit digital messages comprising lighting control instructions for controlling the lighting load via the lighting device. The remote control device may communicate with the lighting device via an intermediary device, such as a hub device. The remote control device may detect a user interface event, such as a button press or a rotation of the remote control device. The remote control device or the hub device may determine whether to transmit digital messages to as unicast messages or multicast messages based on the type of user interface event detected.

Abstract: A surgical device comprising a first jaw member, a second jaw member, a clamping member and a clamp apparatus is disclosed. The clamping member is slidably positioned to translate at least partially through the first jaw member. The clamping member engages the first jaw member and the second jaw member, and has a knife blade for cutting tissue. A flange of the clamping member is configured to engage a cam surface to pivot the second jaw member with respect to the first jaw member from an open position toward an approximated position. The clamp apparatus is movable from a retracted position to an advanced position for preventing a gap between proximal portions of the first jaw member and the second jaw member from exceeding a predetermined distance. The clamping member and the clamp apparatus are separately movable.

Abstract: An aircraft that is convertible between a helicopter mode and an airplane mode. The aircraft includes a fuselage with a longitudinal axis and a vertical axis and distributed propulsion array that surrounds the vertical axis when the aircraft is operating the helicopter mode and surrounds the longitudinal axis when the aircraft is operating in the airplane mode.