- B64C27/001： .{减振装置}
- B64C27/006： .{保护装置}
- B64C27/008： .{旋翼跟踪或平衡装置}
- B64C27/02： .旋翼飞机
- B64C27/04： .直升飞机
- B64C27/20： .以具有带罩旋翼,例如飞行平台为特点的旋翼机
- B64C27/22： .混合式旋翼机,即飞行中利用飞机和旋翼机两者特征的飞行器
- B64C27/32： .旋翼(旋翼和螺旋桨共有的特征入B64C11/00)
- B64C27/51： .{叶片运动的减震}
- B64C27/52： .整个旋翼相对机身的倾斜(翘翘板型结构入B64C27/43)
- B64C27/54： .用于控制叶片相对于旋翼毂的调节或运动,例如滞后提前运动的机构
- B64C27/82： .以装有用于平衡升力旋翼扭矩或改变旋翼机方向的辅助旋翼或流体喷射装置为特点的
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 241 | POWER SAFETY INSTRUMENT SYSTEM | EP10861026.2 | 2010-12-22 | EP2635874A1 | 2013-09-11 | 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. | ||||||
| 242 | Device for supplying electricity | EP07110337.8 | 2007-06-15 | EP2003054A1 | 2008-12-17 | Nilsson, Bernt |
The present invention relates to device (10) for supplying electricity to electrical equipment on a first element (3) drivable for rotating operation with a predetermined rotation rate. Said device (10) comprises an electricity producing means (11) provided with a stator and a rotor that are rotatable in relation to each other. One of the rotor and stator is attached to said first element (3) and the other to a second element (14) provided with at least one braking member (16). In accordance with a predetermined drag coefficient Cd, when interacting with a surrounding fluid medium in rotating operation a braking torque TAB is induced, which results in a difference fdiff in rotation rate between the first element (3) and said second element (14). An output PG to said electricity producing means (11) is based on the product of said braking torque TAB and said rotation rate difference fdiff.
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| 243 | Einrichtung zum Verriegeln | EP00104725.7 | 2000-03-04 | EP1035366A3 | 2002-12-04 | Schreiber, Thomas; Röhn, Torsten |
Die Erfindung geht aus von einer Einrichtung (6) zum Verriegeln eines Aktuators (1) mit einem in einem Zylinder (2) geführten Stellkolben (3), der eine sich zum Mantel hin keilförmig erweiternde Ringnut (5) aufweist, in die mindestens ein durch eine Feder (14) belasteter Verriegelungsbolzen (9) radial eingreift, wobei eine Hilfskraft den Verriegelungsbolzen (9) im Betriebszustand des Aktuators (1) außer Eingriff bringt, indem sie die Feder (14) weiter vorspannt. Es wird vorgeschlagen, daß der Verriegelungsbolzen (9) eine zu seiner Längsachse (27) in Entriegelungsrichtung (28) geneigte Anlagefläche (12) aufweist, an der Fangklauen (15) anliegen und die von einem elektrischen Stellelement (19) in eine entriegelte Position gebracht und festgesetzt wird, wobei erregte Elektromagnete (24) eine Selbsthemmung an der Anlagefläche (12) des Verriegelungsbolzens (9) erzeugen. Die Einrichtung ist insbesondere zum Verriegeln von Aktuatoren (1) geeignet, die mit elektrischer Energie betrieben werden. |
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| 244 | Dispositif de visée pour aéronef à voilure tournante | EP93400619.8 | 1993-03-11 | EP0562899A1 | 1993-09-29 | Jalaguier, Jean Pierre; Krysinski, Tomasz |
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| 245 | Procédé et dispositif pour annuler le potentiel électrostatique d'un hélicoptère par rapport à la terre | EP85400970.1 | 1985-05-15 | EP0161993B1 | 1988-01-20 | Taillet, Joseph |
| 246 | VARIABLE SPEED AIRCRAFT TRANSMISSION | EP15163258.5 | 2015-04-10 | EP2930398B1 | 2018-04-04 | Modrzejewski, Brian Stanley; Mueller, Russell; Mueller, Doug; Woods, Ron; Cecil, Tim |
| A variable state planetary shifting transmission 401 can include an input shaft 501, an output shaft 513; and a planetary system 419 having a sun gear 511 associated with the input shaft, a planetary carrier 507, and a ring gear 523 associated with a ring housing 509. The transmission can include an overrunning clutch 413 operably coupled to the planetary carrier. The transmission can include a clutch assembly 517 coupled to the planetary carrier. The transmission is capable of changing the speed ratio between the input shaft and the output shaft by selective engagement of the clutch assembly against the ring gear which can cause either the freeing or locking of the planetary carrier by the overrunning clutch. | ||||||
| 247 | PROCEDE DE PILOTAGE ASSISTE D'UN AERONEF A VOILURE TOURNANTE COMPRENANT AU MOINS UNE HELICE PROPULSIVE, DISPOSITIF DE PILOTAGE ASSISTE ET AERONEF | EP17175700.8 | 2012-10-26 | EP3242181A1 | 2017-11-08 | SALESSE-LAVERGNE, Marc; QUEIRAS, Nicolas; EGLIN, Paul |
La présente invention concerne un dispositif (10) de pilotage assisté d'un aéronef muni d'une voilure tournante comprenant une pluralité de deuxièmes pales (3'), et d'un groupe propulsif comprenant une pluralité de premières pales (2'). Ce dispositif comporte un moyen de commande (30, 40) pour fournir un ordre de déplacement (O) selon une direction, ledit dispositif (10) ayant une unité de traitement (20) pour transformer ledit ordre (O) en une consigne d'accélération (C) selon ladite direction, puis pour transformer cette consigne d'accélération (C) en au moins une consigne de tenue d'assiette longitudinale (θ*) transmise à un premier système automatique de tenue d'assiette longitudinale (26) contrôlant un pas cyclique longitudinal des deuxièmes pales (3') et une première consigne de tenue de facteur de charge (Nx*) dans une direction longitudinale transmise à un deuxième système automatique (25) de tenue de facteur de charge contrôlant le pas collectif des premières pales (2').
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| 248 | ROTORCRAFT FUEL SYSTEM HAVING ENHANCED CRASH RESISTANCE | EP16172307.7 | 2016-05-31 | EP3241756A1 | 2017-11-08 | PERYEA, Martin; SMITH, Michael Reaugh; HAMELWRIGHT Jr., Douglas; BRAND, Albert G.; PLAGIANOS, Nicholas J.; EMRICH, Joshua; CARR, Timothy |
A rotorcraft (10) includes a fuselage (16) having a fuel tank receiving assembly (24) with a fuel tank (28) positioned therein. The fuel tank (28) including a plurality of interconnected fuel bags operable to contain liquid fuel. A network of straps is disposed about the fuel tank (28) forming a restraint assembly (130; 172; 182; 202). The network of straps includes at least one perimeter strap (132, 134, 136, 138, 140) extending at least partially about at least two fuel bags and at least one surrounding strap (142, 144, 146) extending at least partially about the at least two fuel bags. The at least one perimeter strap (132, 134, 136, 138, 140) has at least two intersections (156, 158) with the at least one surrounding strap (142, 144, 146).
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| 249 | BUBBLE COLLECTOR FOR SUCTION FUEL SYSTEM | EP14873347 | 2014-10-06 | EP3077290A4 | 2017-08-09 | SMITH DAVID R; SHIELDS DANIEL JOHN |
| A fuel feed system for a rotary-winged aircraft includes a fuel feed line extending from a fuel source to an engine and an engine fuel suction pump disposed at the fuel feed line to urge a flow of fuel through the fuel feed line to the engine. A collector is located along the fuel feed line between the fuel source and the engine to collect air-vapor bubbles which form in the flow of fuel. An air-vapor line extends from the top of the collector and merges with the fuel line section between the collector and the engine fuel pump. The air-vapor line is sized and configured to limit the flow of air-vapor from the collector to the engine fuel suction pump to a rate which the engine fuel suction pump can tolerate. | ||||||
| 250 | UNMANNED AERIAL COPTER FOR PHOTOGRAPHY AND/OR VIDEOGRAPHY | EP15795669.9 | 2015-05-22 | EP3145811A1 | 2017-03-29 | BRADLOW, Henry W.; BALARESQUE, Antoine; ENGLIN, Robert N. |
| An unmanned aerial vehicle (UAV) copter for consumer photography or videography can be launched by a user throwing the UAV copter into mid-air. The UAV copter can detect that the UAV copter has been thrown upward while propeller drivers of the UAV copter are inert. In response to detecting that the UAV copter has been thrown upward, the UAV copter can compute power adjustments for propeller drivers of the UAV copter to have the UAV copter reach a predetermined elevation above an operator device. The UAV copter can then supply power to the propeller drivers in accordance with the computed power adjustments. | ||||||
| 251 | STOCKAGE D'ENERGIE A PILES THERMIQUES POUR AERONEF A VOILURE TOURNANTE | EP16178931.8 | 2016-07-12 | EP3125343A1 | 2017-02-01 | CONNAULTE, Matthieu |
L'invention concerne un aéronef (1) à voilure tournante équipé d'une installation électrique (8) comportant au moins une pile thermique (10) d'alimentation d'au moins un équipement consommateur (9) d'énergie électrique. Des spécifications techniques de la pile thermique (10) prévoient : une puissance utile à fournir audit équipement consommateur, entre 20 Watts et 200 kilowatts, un laps de temps de montée en puissance compris entre 3 secondes et 30 secondes, un bas temps de fonctionnement de fourniture utile d'une quantité prédéterminée d'énergie électrique compris entre 10 secondes et 180 secondes. L'invention s'applique notamment aux aéronefs (1) à voilures tournantes.
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| 252 | AIRCRAFT STRUCTURAL COMPONENT ADAPTED FOR ABSORBING AND TRANSMITTING FORCES | EP15400026.9 | 2015-06-29 | EP3112254A1 | 2017-01-04 | Von-Wilmowsky, Kaspar; Reichensperger, Christian; Rack, Andreas |
The invention is related to an aircraft structural component (8a) that is adapted for absorbing and transmitting forces in an aircraft, said aircraft structural component (8a) comprising at least one panel element (10) and at least one reinforcing structure (9). Said at least one reinforcing structure (9) is rigidly attached to said at least one panel element (10) such that at least one cavity (21) is defined between said at least one panel element (10) and said at least one reinforcing structure (9), said at least one cavity (21) being adapted for distributing forces that are absorbed by said aircraft structural component (8a) in operation.
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| 253 | Anti-clog and non-metallic debris detector for lubrication system inlet | EP14191854.0 | 2014-11-05 | EP2871479B1 | 2016-07-20 | Hodgkinson, Eric James; Lutian, David M. |
| 254 | MOBILE GLISSANT, NOTAMMENT HYDROFOIL, À PROPULSION PAR UN DRONE À VOILURE TOURNANTE | EP15197333.6 | 2015-12-01 | EP3031504A1 | 2016-06-15 | SEYDOUX, Henri; ETCHEPARRE, Jean |
Le mobile comprenant une structure statique glissante (100) pourvue dans une région inférieure, d'un ensemble d'éléments de glissement (110, 120g, 120d). Il comprend en outre des moyens (300) pour le montage amovible d'un drone à voilure tournante à rotors multiples (221-224) formant groupe propulseur (200), dont les rotors exercent chacun une poussée avec une composante selon un axe principal (X-X) de glissement du mobile, la commande proportionnelle et individualisée des rotors (221-224) permettant le pilotage du mobile en vitesse et en direction sans gouvernail.
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| 255 | An airfoil blade of a bearingless rotor of a helicopter | EP12400012.6 | 2012-04-18 | EP2653383B1 | 2016-04-13 | Kuntze-Fechner, Gerald; Bauer, Markus; Ortner, Martin |
| 256 | ROTORCRAFT FLIGHT PARAMETER ESTIMATION | EP15163130.6 | 2015-04-10 | EP2955106A1 | 2015-12-16 | Sane, Harshard S.; Driscoll, Joseph T.; Cherepinsky, Igor |
An aircraft is provided and includes an airframe. The airframe includes first and second rotor apparatuses at upper and tail portions of the aircraft, respectively, to provide for control and navigational drive. The aircraft further includes a stabilizer component disposed at the tail portion in a position displaced from downwash of the first and second rotor apparatuses at airspeed ranges and a control system configured to apply a dither actuation signal to the stabilizer component at the airspeed ranges by which an aircraft response to a stabilizer component input is measurable for airspeed estimation purposes.
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| 257 | Anti-clog and non-metallic debris detector for lubrication system inlet | EP14191854.0 | 2014-11-05 | EP2871479A3 | 2015-07-01 | Hodgkinson, Eric James; Lutian, David M. |
A contaminant detection system for use in a fluid distribution system includes a first detector assembly including an inlet housing and detector screen through which fluid in the fluid distribution system passes and a first sensor to detect a first type of contaminant caught in the detector screen; and a second detector assembly including a second sensor which activates when the inlet housing or detector screen is clogged to detect whether the fluid contains a second type of contaminant when the first sensor does not detect the first type of contaminant.
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| 258 | Anti-clog and non-metallic debris detector for lubrication system inlet | EP14191854.0 | 2014-11-05 | EP2871479A2 | 2015-05-13 | Hodgkinson, Eric James; Lutian, David M. |
A contaminant detection system for use in a fluid distribution system includes a first detector assembly including an inlet housing and detector screen through which fluid in the fluid distribution system passes and a first sensor to detect a first type of contaminant caught in the detector screen; and a second detector assembly including a second sensor which activates when the inlet housing or detector screen is clogged to detect whether the fluid contains a second type of contaminant when the first sensor does not detect the first type of contaminant.
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| 259 | Debris detector for non-ferrous bearings | EP13166913.7 | 2013-05-07 | EP2793023B1 | 2015-01-21 | McCollough, James M; Ehinger, Ryan T; Bunch, Troy |
| A system (301) and method to detect non-ferrous debris from a non-ferrous roller bearing element, such as used for lubricating the rotor system of an aircraft . The system (301) includes a trap (303) in fluid communication with a lubrication fluid of the non-ferrous bearing and a sensor (307) operably associated with the trap (303). The method includes trapping the non-ferrous material debris in the lubrication fluid with the trap (303) and triggering the sensor (307) upon detection of the non-ferrous material debris trapped within the trap (303). Changes in the pressure of the lubrication fluid are compensated by balancing the force undergone by the trap with a force applied to a compensator linked mechanically to the trap and having an orifice whose size can be adjusted based on lubricant pressure. | ||||||
| 260 | AIRCRAFT FOR VERTICAL TAKE-OFF AND LANDING WITH TWO WING ARRANGEMENTS | EP13710309.9 | 2013-02-13 | EP2814735A1 | 2014-12-24 | Reiter, Johannes |
| The present invention relates to an aircraft comprising a fuselage (100) comprising a fuselage axis (101), a first wing arrangement (110) and a second wing arrangement (120). The first wing arrangement (110) is mounted to the fuselage (100) such that the first wing arrangement (110) is tiltable around a first longitudinal wing axis (111) of the first wing arrangement (110) and such that the first wing arrangement (110) is rotatable around the fuselage axis (101). The second wing arrangement (120) comprises at least one propulsion unit (122), wherein the second wing arrangement (120) is mounted to the fuselage (100) such that the second wing arrangement (120) is tiltable around a second longitudinal wing axis (121) of the second wing arrangement (120) and such that the second wing arrangement (120) is rotatable around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are adapted in such a way that, in a fixed-wing flight mode, the first wing arrangement (110) and the second wing arrangement (120) do not rotate around the fuselage axis (101). The first wing arrangement (110) and the second wing arrangement (120) are further adapted in such a way that, in a hover flight mode, the first wing arrangement (110) and the second wing arrangement (120) are tilted around the respective first longitudinal wing axis (111) and the respective second longitudinal wing axis (121) with respect to its orientations in the fixed-wing flight mode and that the first wing arrangement (110) and the second wing arrangement (120) rotate around the fuselage axis (101). | ||||||
