Abstract: A method and system for improved performance of a V/STOL aircraft characterized by directing a major portion of exhaust gas flow from a propulsion system through a closed conduit means to exit through a thrust producing primary nozzle that includes turning apparatus for forming a bend for the exhaust flow downstream of the propulsion source; turning the exhaust flow while simultaneously bleeding-off through at least one secondary nozzle a second and minor portion of the exhaust flow from an outer portion of the bend downstream of the bend leasing edge to reduce the vortex formation in the bend and directing the bleed-off and exhaust flows adjacent each other and oriented in the same direction in all flight modes for recovery of the maximum thrust potential.

Abstract: A method and apparatus for starting and stopping the flow of ink from an ink jet printer having a plurality of ink jet orifices through which streams of droplets of ink continuously issue, charge electrodes, deflection electrodes and a drop catcher. An elongated nozzle extends along the length of the orifices and directs an air flow therefrom against the streams of ink issuing from the orifices so as to divert the stream into the catcher to prevent any ink droplets from falling on the media to be printed upon.

Abstract: A propulsion system for an airplane to permit it to achieve vertical and/or short take-offs and landings. The propulsion system is integrated into a wing/nacelle unit and includes a thrust vectoring system. A separate flow turbofan engine is mounted in each wing/nacelle unit. A system of three flaps is located at the rear of each wing/nacelle unit for deflecting the turbofan engine exhaust downward, rearward, or any angle in between. These three flaps are arranged to provide a main thrust nozzle in the horizontal flight position without any additional flaps between them. One flap is located at the wing/nacelle upper surface trailing edge. Two slots are provided at the leading edge of this flap. The upper forward most slot is provided as an exit nozzle for the engine turbine exhaust, which is shrouded from the fan exhaust. The second of these two slots removes a portion of the high energy fan exhaust from the fan discharge duct and ejects it over the flap upper surface.

Abstract: A propulsion system for an airplane to permit it to achieve vertical and/or short take-offs and landings. The propulsion system is integrated into a wing/nacelle unit and includes a thrust vectoring system. A separate flow turbofan engine is mounted in each wing/nacelle unit. A system of three flaps is located at the rear of each wing/nacelle unit for deflecting the turbofan engine exhaust downward, rearward, or any angle in between. These three flaps are arranged to provide a main thrust nozzle in the horizontal flight position without any additional flaps between them. One flap is located at the wing/nacelle upper surface trailing edge. Two slots are provided at the leading edge of this flap. The upper forward most slot is provided as an exit nozzle for the engine turbine exhaust, which is shrouded from the fan exhaust. The second of these two slots removes a portion of the high energy fan exhaust from the fan discharge duct and ejects it over a flap upper surface.