Abstract: An organic photodetector includes an anode and a cathode facing each other and an active layer between the anode and the cathode and including a p-type semiconductor and an n-type semiconductor, wherein an energy barrier between the anode or the cathode and the active layer is greater than or equal to about 1.3 eV, a difference between a HOMO energy level of the p-type semiconductor and a LUMO energy level of the n-type semiconductor is greater than or equal to about 0.8 eV.

Abstract: An organic photodetector includes an anode and a cathode facing each other and an active layer between the anode and the cathode and including a p-type semiconductor and an n-type semiconductor, wherein an energy barrier between the anode or the cathode and the active layer is greater than or equal to about 1.3 eV, a difference between a HOMO energy level of the p-type semiconductor and a LUMO energy level of the n-type semiconductor is greater than or equal to about 0.8 eV.

Abstract: An organic electronic device includes an organic device including an organic material, a first protective film on the organic device, a second protective film on the first protective film and including a same material as the first protective film, and a third protective film on the second protective film.

Abstract: Provided are a color-depth sensor and a three-dimensional image acquisition apparatus including the same. The color-depth sensor includes a color sensor that senses visible light and an infrared sensor that is stacked on the color sensor and senses infrared light. The 3D image acquisition apparatus includes: an imaging lens unit; a color-depth sensor that simultaneously senses color image information and depth image information about an object from light reflected by the object and transmitted through the imaging lens unit; and a 3D image processor that generates 3D image information by using the color image information and the depth image information sensed by the color-depth sensor.

Abstract: An aircraft converting aerodynamic compression ram thermal stream energy into thrust power generation comprising:(a) an aerodynamic compression ram thermal stream generating multiple vane diffuser as the air-inlet to a pressure plenum;(b) a ram thermal-pressure stream induction double throttle duct consisting of a main ramflow inducing nozzle and a fuel injection ramflow inducing nozzle wihch coalesce to form the air-oulet of a pressure plenum-engine pod;(c) a compressed air shooting annular slotted ignition chamber downstream of the fuel injecting ramflow inducing nozzle with flame bed-walled combustion chamber forming a ramjet engine;(d) a ram thermal-pressure stream induction annular slotted thrust nozzle extending rearward from the combustion chamber of the ramjets and exit nozzle of a turbojet engine thereby creating a tailpipe for the turbo-ram induction jet engine; and(e) an aerodynamic compression ram thermal stream sink double-walled shockcone airframe, the double walled shockcone housing the ram the

Abstract: An induction lift flying saucer having a circular shaped air frame which houses a vacuum cell induction lift wing adapted to be used in an aerodynamic generating channel wherein the lift wing includes an airfoil having a leading edge and a trailing edge, a top panel and an acoustically treated hollow interior, and wherein the airfoil includes airtight partitions forming individual cells within the hollow interior and the airfoil has inclined slots extending from the top panel into each of the individual cells wherein the inclined slots extend at an angle from each of the individual cells toward the trailing edge of the airfoil and wherein the airfoil is adapted to be positioned within an aerodynamic generating channel with the top panel of the airfoil being adapted to form a lower boundary of the aerodynamic generating channel and to define a slip thereacross from an airstream passing through the aerodynamic generating channel, a bearing support operatively coupled to the airfoil adjacent the trailing edge to

Abstract: An ultra hypersonic aircraft having aerodynamic heat transferring pipes forming an airframe structure is shown. The heat transformer pipes include a high pressure steam generator located at the forward section thereof and a low pressure steam condensator located at the rearward section thereof. Low pressure water is circulated between the rearward section and the forward section for heat balancing of the air frame structure and for operating the room air conditioning system of an aircraft. A steam pressure reactant turbine, which drives an electric generator, is used as a boundary between the high and low pressure steam sections. The electric generator provided electrical and power supply for the infrared or arc heaters, and electric heaters recessed in the ceiling and wall panels of an acrodynamic lift-thrust generating channel for back-heating of the turbo-ram oval thrust stream in the thrust generating channel of a hypersonic aircraft.

Abstract: A ram constriction vane diffuser adapted as an air intake of an air plenum-engine pod wherein vertical multiple vanes are fitted on the vertically inclined air intake opening and include fixed vanes positioned adjacent the centerline portion of the air plenums which define an envelope for the airflow including nozzles locate on both sides of a jet engine, a plurality of deflectable vanes positioned in an equally spaced relationship in the air intake openings on both sides of fixed vanes, and wherein each deflectable vane has a leading edge and a drivable trailing section pivotally mounted on the rigid leading section of the deflectable vane and with the drivable trailing sections of each vane and with an actuator for adjusting the angle of the deflectable vanes relative to the freestream air flow for enabling the drivable trailing section of each vane to be turned away from a parallel position to the centerline of an engine suction diffuser, which is the original position thereof for speed flight, to reduce t

Abstract: A vacuum cell induction lift wing adapted to be used in an aerodynamic generating channel wherein the lift wing includes an airfoil having a leading edge and a trailing edge and a top panel and an acoustically treated hollow interior, and wherein the airfoil includes airtight partitions forming individual cells within the hollow interior and the airfoil has inclined slots extending from the top panel into each of the individual cells wherein the inclined slots extend at an angle from each of the individual cells toward the trailing edge of the airfoil and wherein the airfoil is adapted to be positioned within an aerodynamic generating with the top panel of the airfoil being adapted to form a lower boundary of the aerodynamic generating channel and to define a slip thereacross from an airstream support operatively coupled to the airfoil adjacent the trailing edge to enable the airfoil to be rotated therearound to change the angle of incidence of the top panel to an airstream passing thereacross and a pivot sup

Abstract: An aerodynamic heated steam generating apparatus having an aerodynamic heat immersion coil steam generator adapted to be located on the leading edge of an airframe of a hypersonic aircraft and being responsive to aerodynamic heating of water by a compression shock airstream to produce the steam pressure, expansion shock air-cooled condenser adapted to be located in the airframe rearward of and operatively coupled to the aerodynamic heat immersion coil steam generator to receive and condense the steam pressure, a steam pressure reacting device operatively coupled between the aerodynamic heat immersion coil steam generator and the expansion shock air-cooled condenser for driving a load and an aerodynamic heated steam injector manifold adapted to distribute heated steam into the airstream flowing through an exterior thrust generating channel of an air-breathing, ducted power plant is shown.

Abstract: A liquid fuel prevaporization and backburning induction jet thrust transition tailpipe having a primary inlet adapted to be affixed to a turbojet engine and having a diverging area in the transition tailpipe formed of vertically converging and horizontally diverging walls terminating in a thrust nozzle, a pair of air plenums for directing an air/ram flow into the main airflow path having a bellmouth shaped inlet which communicates with an airflow inducing nozzle which terminates in a chamber having a downstream end opening forming a secondary inlet to the diverging area, a plurality of parallel, vertically spaced curved inductor vanes positioned in the secondary inlets and which are adapted to deflect a secondary airflow passing through the bellmouth shaped airflow inducing nozzle, chamber and secondary inlet into a path through the diverging area which is substantially directed towards the thrust nozzle, an upper and lower liquid fuel prevaporization chambers, fuel injectors, and gas outlets, a vaporized gas

Abstract: A shockcone and channeled disk-airframe having a top airfoil disk and lower airfoil disk comprising a wedge perimeter extending from the forward nose of a shockcone and therearound the leading edge to the trailing edge of an airframe body wherein the lower part of disk-airframe has a plurality of bottomwardly opened channels extending from the leading to the trailing edge whereto providing the channel walls. The disk-airframe has a plurality of inclined rudders operatively coupled to the vertical fins located rear on both sides of the top airfoil disk-airframe. The airframe is mushroom in sectional shape; the stem of the mushroom is the lower part of a disk-airframe and forms the depth of the fuselage and the walls of channels and the cap of the mushroom is the top airfoil disk which is convex from the wedge perimeter of the airframe within the upper part and providing the cargo space of a disk-airframe. The size of the channels is a minimum 50 percent of the width of the disk-airframe.