IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0442903
(2003-05-22)
|
등록번호 |
US-7281680
(2007-10-16)
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발명자
/ 주소 |
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
6 인용 특허 :
2 |
초록
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The aircraft incorporates a single ducted propeller. The fuselage Bridges over the ducted propeller assembly, and is shaped in a way that the incoming air can smoothly flow into the propeller area. The duct has an aerodynamically shaped frontal area, and an aft extension, which forms the tail sectio
The aircraft incorporates a single ducted propeller. The fuselage Bridges over the ducted propeller assembly, and is shaped in a way that the incoming air can smoothly flow into the propeller area. The duct has an aerodynamically shaped frontal area, and an aft extension, which forms the tail section. The wings are attached to the side of the duct. The ducted propeller assembly also contains louvers, which run span wise, to redirect the outgoing air in horizontal direction. During vertical take-off or landing, the propeller has a horizontal plane of rotation, after take-off the whole craft entirely tilts forward approximately 26 degrees to transition into horizontal wing born flight. During vertical flight, the aircraft is controlled by control louvers installed inside the ducted propeller assembly in the propeller slipstream.
대표청구항
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Having described my invention, I now claim: 1. An aircraft equipped with only a single propeller and only a single duct, capable of short or vertical take-off and landing (S/VTOL) as well as an efficient horizontal cruise mode comprising: a fuselage or cabin section where said fuselage transverse c
Having described my invention, I now claim: 1. An aircraft equipped with only a single propeller and only a single duct, capable of short or vertical take-off and landing (S/VTOL) as well as an efficient horizontal cruise mode comprising: a fuselage or cabin section where said fuselage transverse cross section has a symmetrical air foil shape where the sharp edge forms the bottom of the fuselage and is attached to the top section of said single duct; a propulsion assembly comprising a single propeller installed horizontally inside the single duct, said propeller having a propeller shaft, where said shaft is mounted vertically into the bottom of said fuselage, via bearings and bearing housing, where the aircraft center of gravity is located; a pair of wings mounted on opposing lateral sides of said single duct, said wings having left and right ailerons for roll control during horizontal flight; an aft extension of said single duct forming a tail surface, which supports an elevator to control the pitch during horizontal flight, said tail surface also supports at least one vertical tail surface to provide for directional stability and to control yaw during horizontal flight; a set of landing gears one installed in the front section of said fuselage, and a pair of gears installed in the rear section of said tail surface. 2. The S/VTOL aircraft of claim 1 further comprising a plurality of louvers installed span wise inside said single duct in the propeller slipstream for redirecting the exiting airflow, said louvers are operable simultaneously to redirect substantially all thrust in an aft ward airframe referenced generally horizontal direction during horizontal flight to improve the horizontal speed. 3. The S/VTOL aircraft of claim 2 wherein said louvers are interconnected by control rods, said control rods being attached perpendicularly to the trailing edge of said louvers, and being operated simultaneously, said louvers having an airfoil shape in cross section, having a chord vertically oriented in a vertical take-off and lading mode, said louvers being pivoted around a longitudinal axis via bearings mounted in said single duct. 4. The S/VTOL aircraft of claim 3 wherein said pivoting louvers have a range of movement approximately 30 degrees and have a vertical position in a vertical flight mode, said louvers reach their maximum tilting range and are stopped by stopping blocks installed on the walls of said duct. 5. The S/VTOL aircraft of claim 4 wherein said pivoting louvers reach said stopping blocks in the horizontal flight mode, said louvers are constructed in a way that they can be further bent to the point where they direct the airflow exiting said louvers in aft ward horizontal direction to achieve a smooth airflow therefore the thrust created by the propeller will have mainly horizontal components for high speed flight. 6. The S/VTOL aircraft of claim 1 wherein said propulsion assembly incorporating a single propeller further comprising at least one engine having an output shaft connected to a beveled gear assembly, and said propeller shaft for powering said propeller to produce thrust. 7. The S/VTOL aircraft of claim 1 further comprising a control system to control and stabilize the single propeller and single duct aircraft during hover and transition flight; said control system comprising; at least one control louver mounted in the front section of said single duct, operating in the propeller slipstream said control louver is mechanically connected to said elevator via push-pull rods to produce nose down pitch, by pivoting forward, and therefore creating turbulence and down force on the front section of said single duct; a control louver mounted in the rear section of said single duct, operating in the propeller slipstream, said control louver is mechanically connected to said elevator via push-pull rods to produce tail down pitch, by pivoting aft ward, and therefore creating turbulence and down force on the rear section of said single duct; a left control spoiler mounted on the left side of said single duct operating in the propeller slip stream said left control spoiler is mechanically connected to the left aileron via push-pull rods to produce roll by pivoting, and therefore creating turbulence and left down force on said single duct, rolling the aircraft to the left; a right control spoiler mounted on the right side of said single duct operating in the propeller slipstream, said right control spoiler is mechanically connected to the right aileron via push-pull rods to produce roll by pivoting, and therefore creating turbulence and right down force on said single duct, rolling the aircraft to the right; a pair of control louvers running diagonally through the central section of said single duct operating in the propeller slipstream where said control louvers are separated at the propeller shaft to form a left control louver and a right control louver, where said left control louver is pivoting to create a component of forward thrust, and at the same time a right control louver is pivoting to create a component of rearward thrust, therefore making the aircraft yaw to the left, or if the pivoting of said control louvers is reversed the aircraft will yaw to the right.
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