Abstract: An aircraft includes a fuselage coupled to a wing having a root section and first and second outboard sections each having first and second wing layers pivotably coupled to respective outboard ends of the root section. A thrust array is coupled to the wing. A power system is operably associated with the thrust array to provide power to each of a plurality of propulsion assemblies. A flight control system is operably associated with the thrust array and the wing. The flight control system is operable to control the thrust output from the propulsion assemblies and the configuration of the wing. In a thrust-borne vertical lift mode, the wing has a split wing configuration such that the thrust array forms a two dimensional thrust array. In the wing-borne forward flight mode, the wing has a monoplane configuration such that the thrust array forms a one dimensional thrust array.

Abstract: An aircraft includes a fuselage coupled to a wing having a dihedral root section with first and second outboard sections pivotably coupled to respective outboard ends thereof. A thrust array is coupled to the wing. A power system is operably associated with the thrust array to provide power to each of a plurality of propulsion assemblies. A flight control system is operably associated with the thrust array and the wing. The flight control system is operable to control the thrust output from the propulsion assemblies and the configuration of the wing. In a thrust-borne vertical lift mode, the wing has an M-wing configuration with the center of gravity of the aircraft located between the outboard sections of the wing. In a wing-borne forward flight mode, the wing has a gull wing configuration with the center of gravity of the aircraft located below the outboard sections of the wing.

Abstract: An aircraft includes a fuselage coupled to a wing having a root section and first and second outboard sections each having first and second wing layers pivotably coupled to respective outboard ends of the root section. A thrust array is coupled to the wing. A power system is operably associated with the thrust array to provide power to each of a plurality of propulsion assemblies. A flight control system is operably associated with the thrust array and the wing. The flight control system is operable to control the thrust output from the propulsion assemblies and the configuration of the wing. In a thrust-borne vertical lift mode, the wing has a split wing configuration such that the thrust array forms a two dimensional thrust array. In the wing-borne forward flight mode, the wing has a monoplane configuration such that the thrust array forms a one dimensional thrust array.

Abstract: An aircraft includes a fuselage coupled to a wing having a dihedral root section with first and second outboard sections pivotably coupled to respective outboard ends thereof. A thrust array is coupled to the wing. A power system is operably associated with the thrust array to provide power to each of a plurality of propulsion assemblies. A flight control system is operably associated with the thrust array and the wing. The flight control system is operable to control the thrust output from the propulsion assemblies and the configuration of the wing. In a thrust-borne vertical lift mode, the wing has an M-wing configuration with the center of gravity of the aircraft located between the outboard sections of the wing. In a wing-borne forward flight mode, the wing has a gull wing configuration with the center of gravity of the aircraft located below the outboard sections of the wing.

Abstract: The invention relates generally to a system and method for testing fuel evaporative systems, and more particularly to a stand-alone tank tester system (and method) for testing vehicle fuel tank integrity. Furthermore, a self-contained calibration tank with switchable leak sizes for calibrating the tank tester to multiple leak sizes is provided. Constant flow and vacuum methods for testing fuel tank integrity are also provided.

Abstract: The invention relates generally to a system and method for testing fuel evaporative systems, and more particularly to a stand-alone tank tester system (and method) for testing vehicle fuel tank integrity. Furthermore, a self-contained calibration tank with switchable leak sizes for calibrating the tank tester to multiple leak sizes is provided. Constant flow and vacuum methods for testing fuel tank integrity are also provided.

Abstract: A fuel cell stabilisation system for stabilising the supply of electrical power from a fuel cell stack (101) to a DC bus (104), including: a DC power supply (108); and a control (112) configured to enable the DC power supply (108) to supply electrical power to the DC bus (104).

Abstract: The invention relates generally to a system and method for testing fuel evaporative systems, and more particularly to a stand-alone tank tester system (and method) for testing vehicle fuel tank integrity. Furthermore, a self-contained calibration tank with switchable leak sizes for calibrating the tank tester to multiple leak sizes is provided. Constant flow and vacuum methods for testing fuel tank integrity are also provided.

Abstract: Side panels for internal combustion engine housings lacking rectilinear access to housing suppress engine noise.

Abstract: The invention relates generally to a system and method for testing fuel evaporative systems, and more particularly to a stand-alone tank tester system (and method) for testing vehicle fuel tank integrity. Furthermore, a self-contained calibration tank with switchable leak sizes for calibrating the tank tester to multiple leak sizes is provided. Constant flow and vacuum methods for testing fuel tank integrity are also provided.