| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | Arrangement of the openings to loading compartments in vertical take off and landing air vehicles | US3561704D | 1968-07-10 | US3561704A | 1971-02-09 | SCHULZE CARSTEN |
| An airplane adapted to vertical take off and landing which includes a fuselage comprising cargo chamber means having opening means for loading cargo into and unloading cargo from said cargo chamber means, and means pivotally connected to said fuselage, said last mentioned means comprising lifting means and simultaneously forming closing hatch means for selectively opening and closing said opening means.
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| 182 | One-man aircraft with jet-powered lift and propulsion | US3506221D | 1968-05-13 | US3506221A | 1970-04-14 | CAILLETTE GEORGES EDMOND; VIDAL JEAN AMABLE |
| 183 | Articulated airfoil vanes | US3442493D | 1965-10-22 | US3442493A | 1969-05-06 | SMITH LEROY H JR |
| 184 | Stabilizing system for aircraft | US54210366 | 1966-04-12 | US3380689A | 1968-04-30 | RUDOLF BUCHER |
| 185 | Vertical rising aerodynamic vehicles | US41595264 | 1964-12-04 | US3297278A | 1967-01-10 | HAWKINS AUGUSTUS S |
| 186 | Combination aircraft | US41406864 | 1964-11-27 | US3282534A | 1966-11-01 | MICHAEL LASCARIS; COSTAS PANDALEON |
| 187 | Vertical take off and landing aircraft | US3104853D | US3104853A | 1963-09-24 | ||
| 188 | Fluid sustained aircraft | US14948761 | 1961-10-30 | US3072366A | 1963-01-08 | ZALLES FREELAND LEONOR |
| 189 | Airplane | US23786127 | 1927-12-05 | US1721772A | 1929-07-23 | DAVIS JOHN H |
| 190 | POWER SAFETY INSTRUMENT SYSTEM | EP17191651.3 | 2010-12-22 | EP3309079A1 | 2018-04-18 | McCOLLOUGH, James; OLTHETEN, Erik; LAPPOS, Nicholas |
A method of providing power information in a rotorcraft, the rotorcraft having a powerplant. The method comprising calculating a real-time power required and calculating a real-time power available, and orienting power required and power available indicators on a power safety instrument, the position of the power required indicator being dependent upon the calculated power required, and the position of the power available indicator being dependent upon the calculated power available.
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| 191 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT | EP15819516.4 | 2015-08-14 | EP3168147A1 | 2017-05-17 | Noroian, Gevorg Serezhaevich |
The invention relates to aviation technology, specifically to vertical take-off and landing aircraft. The vertical take-off and landing aircraft comprises two turbines, the lower of which is of plate-like shape, and the upper is of flat or plate-like shape. Each turbine comprises a reactive power plant. The body of each turbine is mounted on a metallic disc connected to a vertical shaft of the aircraft, and is equipped with vanes. The vanes are mounted such that the position thereof can be changed. The aircraft can comprise intermediate turbines which are mounted between the upper and lower turbine and are flat or plate-like. The reactive power plant of each turbine comprises an air engine and receivers which are connected to a compressor. The body of each turbine is metallic and comprises two rings, one of which is connected to the disc, and also radial struts which are mounted along the perimeter of the turbine body and are connected to the rings and vanes. The vanes are mounted in a single row along the perimeter of the body or are arranged in a single tier. The result is an increase in the reliability and economy of the aircraft, and the possibility of the latter moving vertically, horizontally or at any inclination. |
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| 192 | ROTARY-WING AIR VEHICLE AND METHOD AND APPARATUS FOR LAUNCH AND RECOVERY THEREOF | EP15275222 | 2015-10-30 | EP3162707A1 | 2017-05-03 | |
| A rotary-wing air vehicle comprising a main body (12) and at least two rotor devices (16a, 16b) arranged and configured to generate propulsion and thrust, in use, to lift and propel said air vehicle, said rotor devices (16a, 16b) being arranged and configured relative to said main body (12) such that the blades thereof do not cross through a central vertical axis of said main body (12) defining the centre of mass thereof, wherein said main body (12) is provided with an aperture (100) that extends therethrough to define a channel about said central vertical axis. | ||||||
| 193 | POWER SAFETY INSTRUMENT SYSTEM | EP16180840.7 | 2010-12-22 | EP3124385A1 | 2017-02-01 | McCOLLOUGH, James; OLTHETEN, Erik; LAPPOS, Nicholas |
A method of providing power information in a rotorcraft, the rotorcraft having a powerplant. The method comprising calculating a real-time power required and calculating a real-time power available, and orienting power required and power available indicators on a power safety instrument, the position of the power required indicator being dependent upon the calculated power required, and the position of the power available indicator being dependent upon the calculated power available.
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| 194 | A FLIGHT CONTROL DEVICE FOR AN AIRCRAFT | EP15703959.5 | 2015-02-04 | EP3110691A1 | 2017-01-04 | TILLY, Bruno; RAVOUX, Nicolas |
| The invention relates to a flight control device for an aircraft, the device comprising a mount, a lever pivotally mounted on the mount, and mechanical means for generating a return force for the lever, said means including a spring and a first motor member that are arranged so that a first end of the spring is constrained to move in rotation with the lever and a second end of the spring is constrained to move in rotation with an outlet shaft of the first motor member. According to the invention, the flight control device includes an electrical assistance system for assisting said mechanical means for generating a return force. | ||||||
| 195 | VERTICAL TAKEOFF AND LANDING (VTOL) AIR VEHICLE | EP14828680 | 2014-05-05 | EP2991897A4 | 2016-12-21 | TAYLOR DANA J; TOKUMARU PHILLIP T; HIBBS BART DEAN; PARKS WILLIAM MARTIN; GANZER DAVID WAYNE; FISHER CHRISTOPHER EUGENE; MUKHERJEE JASON SIDHARTHADEV; KING JOSEPH FREDERICK |
| A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing. | ||||||
| 196 | ASSISTED TAKEOFF | EP14887273 | 2014-03-27 | EP2964526A4 | 2016-05-04 | SHI JUN; PAN XU YANG |
| 197 | ASSISTED TAKEOFF | EP14887273.2 | 2014-03-27 | EP2964526A1 | 2016-01-13 | SHI, Jun; PAN, Xu yang |
| Systems，methods，and devices are provided for assisted takeoff of an aerial vehicle．The aerial vehicle may takeoff using a first control scheme and switch to a second control scheme for normal flight when a takeoff threshold is met．The first control scheme optionally does not use Integral control while the second control scheme may use integral control．The aerial vehicle may determine that a takeoff threshold is met (228,230)，based on an out put to a motor of the aerial vehicle and／or an acceleration of the aerial vehicle. | ||||||
| 198 | VTOL aircraft with a thrust-to-weight ratio smaller than 0.1 | EP14075023.3 | 2014-04-17 | EP2933188A1 | 2015-10-21 | Chen, Li Jing |
An aircraft includes: ailerons (1,2); a turbofan engine (3) comprising a high-temp duct (4) with an openable/ closable propelling nozzle (5), and a low-temp duct (6) with an openable/closable propelling nozzle (7); a high-temp bypass duct (9) comprising an openable/closable inlet (8) connected to the high-temp duct(4), an outer wall(10) and a rectangle outlet(12) with a height-to-width ratio smaller than 0.1; a low-temp bypass duct (15) comprising an openable/closable inlet (14) connected to the low-temp duct (7), an outer wall (16), an inner wall (17) and a rectangle outlet (19) with a height-to-width ratio smaller than 0.1. During vertical take-off/lading, closing the propelling nozzles (5, 7) of turbofan engine (3), and opening the inlets (8,14) of high-temp and low-temp bypass ducts(9,15), low-temp planar air jet (20) is cause to flow over upper surface of the aircraft, thereby generating lift and no air flow over lower one.
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| 199 | METHODS AND APPARATUS FOR VERTICAL/SHORT TAKEOFF AND LANDING | EP12849670 | 2012-11-13 | EP2780227A4 | 2015-09-23 | HAYDEN RAYMOND |
| Methods and apparatus for vertical or short takeoff and landing. In one embodiment, the apparatus comprises two or more counter driven rings with one or more airfoils attached. In one variant, there is an upper ring and a lower ring, each with multiple airfoils attached. In one variant, lift is generated largely via ambient air currents, allowing for long term on-station operation of the device. | ||||||
| 200 | POWER SAFETY INSTRUMENT | EP10861026.2 | 2010-12-22 | EP2635874B1 | 2015-07-01 | MCCOLLOUGH, James, M.; OLTHETEN, Erik; LAPPOS, Nicholas |
| A power safety system (301) is configured to provide power information in an aircraft (101). The power safety system (301) includes a power safety instrument (303) having a power required indicator (311) and a power available indicator (313), each being located on a display. A position of the power required indicator (311) and the power available indicator (313) represent the power available and power required to perform a hover flight maneuver. The power safety system (301) may be operated in a flight planning mode or in a current flight mode. The power safety system (301) uses at least one sensor (309) to measure variables having an effect on the power required and the power available. | ||||||
