| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | Aircraft having at least two propeller drive unit disposed spaced apart from each other in the span width direction of the blade | JP2011517043 | 2009-07-13 | JP2011527253A | 2011-10-27 | レクツェー、ダニエル |
| 機体（３）と、それぞれがプロペラ回転軸（１１ａ、１２ａ、１３ａ、１４ａ）を有して翼幅方向において互いに離隔された少なくとも２つのプロペラ駆動部（１１、１２、１３、１４）を収容できる２つの空気力学翼とを有し、プロペラ駆動部（１１、１２、１３、１４）を稼働させるためのコントローラを有する航空機（１）において、推進力を発生させるためのコントローラの１つの作動モードにおいて、各プロペラ回転軸に対して固定されたプロペラの外側部分が機体（３）に面した側において上から下に動かされるように、プロペラ駆動部（１１、１２、１３、１４）が稼働される。 | ||||||
| 22 | Promotion linearization mechanism | JP2003519721 | 2002-08-06 | JP2004537680A | 2004-12-16 | アッシュワース，エリック |
| 流体流動制御機構を流体流動の線形化のために提供する。 該機構は、複数のプロペラ素子をその上に回動可能に支持する円筒状の外側バッフルを有するフレームを含む。 各プロペラ素子は、プロペラ素子が回動する各掃拭域を定義し、該掃拭域は、隣接するプロペラ素子の掃拭域と重複する。 外側バッフルは、各プロペラ素子の集合的掃拭域の外周に外接する。 該プロペラ素子は同方向に回動して、隣接するプロペラ素子の屈曲流動の力が実質的に互いに相殺され、前記機構を通過する流体流動は線形化されるのである。 羽根の非掃拭域内に追加されるバッフルと充填材とを、機構の特定用途のために設けてもよい。 様々な適用においては、接線流動の屈曲力の統合によって、ベクトル流動の線形力が形成され、そして、プロペラ回動平面上の屈曲力ポテンシャルの統合によって、効率流動系が形成され、放出流動と導入流動とを遮断し、これにより、動的流動の直近の流体は、乱されていない静的状態に保たれる。 これによって、流体推進組み立てにあたって、領域の静止帯域の外部効用マントルに備えることが可能となるのである。
【選択図】図１ |
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| 23 | 드론 | KR1020160040958 | 2016-04-04 | KR1020170114354A | 2017-10-16 | 고국원 |
| 본발명의드론은공중부양의대상이되는프레임; 상기프레임의가운데에설치되고회전에의해공중에상기프레임을부양시키는양력을생성하는메인프로펠러; 상기프레임의가장자리에설치되고상기메인프로펠러에의해부양된상기프레임의자세또는이동방향을조절하는복수의서브프로펠러;를포함하고, 각서브프로펠러는상기메인프로펠러의회전축을기준으로서로대칭되는위치에배치될수 있다. | ||||||
| 24 | 회전익 구조체 및 비행 방법 | KR1020140147084 | 2014-10-28 | KR1020160049663A | 2016-05-10 | 김준규; 김형세; 송재민 |
| 본발명은세개의블레이드의회전에의해자유롭게비행할수 있는회전익구조체및 비행방법에관한것으로, 본체로부터서로동일한각도를이루도록방사형으로형성되는고정축을중심으로틸트가능하도록결합되는복수의로터부를구비하여, 복수의로터부에구비되는블레이드를고정축을중심으로각각개별적으로틸트시킴으로써전진, 후진, 좌측또는우측으로이동하고, 요잉제어를할 수있도록구성하여신속한기동력을확보할수 있다. 본발명은회전익구조체의동작을제어하는본체, 본체로부터서로동일한각도를이루도록방사형으로형성되고, 본체와연결되는복수의고정축, 본체의제어에의해복수의고정축을중심으로각각틸트가능하도록복수의고정축에각각결합되며, 서로동일한방향으로회전하는블레이드를구비하여본체에양력을제공하는로터부를포함하는회전익구조체의비행방법으로, 회전익구조체는본체의제어에의해서로동일한방향으로회전하는복수의블레이드의속도를동일하게증가시키며, 복수의블레이드중 선택된적어도하나의블레이드를틸팅시켜요잉제어하여이륙, 공중고정, 착륙하는단계를포함한다. 본발명에따른회전익구조체는복수의로터부를정해진위치에조립하지않고, 구분없이본체에탈착가능하도록구성하여조립및 분해가용이하여보관이용이하고, 휴대성이강조되며, 보호대를통하여블레이드회전에의한안전유해요소를차단할수 있어아동의완구제품부터산업, 국방무기체계에적용할수 있는장점이있다. | ||||||
| 25 | Rotor Assembly having Thrust Vectoring Capabilities | US15606275 | 2017-05-26 | US20180339773A1 | 2018-11-29 | John Richard McCullough; Paul K. Oldroyd; Mark Adam Wiinikka; Jouyoung Jason Choi |
| A rotor assembly for an aircraft is operable to generate a variable thrust vector. The rotor assembly includes a mast that is rotatable about a mast axis. A ball joint is positioned about and non rotatable with the mast. A tilt control assembly is positioned on and has a tilting degree of freedom relative to the ball joint. The tilt control assembly is non rotatable with the mast. A rotor hub is rotatably coupled to the tilt control assembly. The rotor hub is rotatable with the mast in a rotational plane and tiltable with the tilt control assembly. The rotor hub includes a plurality of grips each coupled to a rotor blade. Actuation of the tilt control assembly changes the rotational plane of the rotor hub relative to the mast axis, thereby generating the variable thrust vector. | ||||||
| 26 | Aircraft having Omnidirectional Ground Maneuver Capabilities | US15606197 | 2017-05-26 | US20180339772A1 | 2018-11-29 | John Richard McCullough; Paul K. Oldroyd |
| An aircraft having omnidirectional ground maneuver capabilities. The aircraft includes an airframe and a plurality of propulsion assemblies attached to the airframe. Each of the propulsion assemblies includes a nacelle having a mast axis, a rotor assembly having a tilting degree of freedom relative to the mast axis and a tail assembly rotatable about the mast axis. The tail assembly includes at least one wheel having a rotational axis. A flight control system is operable to independently control each of the propulsion assemblies including tilting each rotor assembly and rotating each tail assembly. For each propulsion assembly, the rotor assembly and the tail assembly have complementary configurations in which a thrust vector generated by the rotor assembly has a horizontal component that is generally perpendicular to the rotational axis of the wheel, thereby enabling omnidirectional ground maneuvers. | ||||||
| 27 | Aircraft with Active Aerosurfaces | US15606163 | 2017-05-26 | US20180339771A1 | 2018-11-29 | Paul K. Oldroyd; John Richard McCullough |
| An aircraft operable to transition between a forward flight mode and a vertical takeoff and landing flight mode. The aircraft includes an airframe having first and second wings. A plurality of propulsion assemblies is attached to the airframe with each of the propulsion assemblies including a nacelle and a tail assembly having at least one active aerosurface. A flight control system is operable to independently control each of the propulsion assemblies. For each of the propulsion assemblies, the tail assembly is rotatable relative to the nacelle such that the active aerosurface has a first orientation generally parallel to the wings and a second orientation generally perpendicular to the wings. | ||||||
| 28 | Systems and Methods for Acoustic Radiation Control | US15588977 | 2017-05-08 | US20180319491A1 | 2018-11-08 | Martin Kearney-Fischer |
| Disclosed is a system for controlling acoustic radiation from an aircraft. The system comprising a plurality of rotor systems (one or more) and a noise controller configured to regulate acoustic radiation from the plurality of rotor systems. The noise controller can be configured to regulate a commanded flight setting from the flight control system and to output a regulated flight setting to the plurality of rotor systems. Based on the regulated flight setting, the plurality of rotor systems are configured to generate, individually and in aggregate, acoustic radiation having a target acoustic behavior. The target acoustic behavior may be achieved using beamforming techniques to, for example, change the directionality of acoustic radiation from the plurality of rotor systems, or otherwise tune the acoustic radiation to reduce detectability and/or annoyance. | ||||||
| 29 | AIRCRAFT AND FLIGHT SYSTEM | US15921881 | 2018-03-15 | US20180265191A1 | 2018-09-20 | Hideomi SAKUMA |
| An aircraft includes propellers at a center of the airframe; a first power source; a pitch adjuster to change pitch angles of the propellers; a plurality of attitude control propellers; a second power source lower in output than the first power source; and a control circuit to control attitude of the airframe. The control circuit includes a first yaw rotation generation control unit to control first yaw rotation generated by torques of the propellers with the pitch adjuster; and a second yaw rotation generation control unit to control a second yaw rotation generated by torques generated by a difference in rotation speed between the attitude control propellers. The control circuit is configured to control the first yaw rotation generation control unit and the second yaw rotation generation control unit in accordance with a magnitude of a command value of yaw rotation. | ||||||
| 30 | TILTROTOR PROPULSION SYSTEM FOR AN AIRCRAFT | US15259596 | 2016-09-08 | US20180065741A1 | 2018-03-08 | Randy M. Vondrell; Matthew Ryan Polakowski; Kurt David Murrow; Glenn Crabtree; Darek Tomasz Zatorski |
| An aircraft includes a fuselage, a forward wing assembly, and aft wing assembly, and a propulsion system. The propulsion system includes a first primary thrust propulsor and a first secondary thrust propulsor, the first primary thrust propulsor being different than the first secondary thrust propulsor. Both the first primary thrust propulsor and the first secondary thrust propulsor are mounted to the same one of: a starboard side of the aft wing assembly, a port side of the aft wing assembly, a starboard side of the forward wing assembly, or a port side of the forward wing assembly. | ||||||
| 31 | DIRECT DRIVE AFT FAN ENGINE | US15240104 | 2016-08-18 | US20180051654A1 | 2018-02-22 | Gabriel L. Suciu; Jesse M. Chandler |
| An aircraft engine includes a gas powered turbine core. A first fan is connected to the turbine core via a shaft. The fan is positioned aft of the turbine. A second fan is connected to the first fan via a geared connection. | ||||||
| 32 | BISTABLE PITCH PROPELLER SYSTEM WITH BIDIRECTIONAL PROPELLER ROTATION | US15225018 | 2016-08-01 | US20180029693A1 | 2018-02-01 | Damon Vander Lind; Todd Reichert |
| A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion of the blade and a second structure coupled to the blade when the blade is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction. | ||||||
| 33 | Vehicle configuration with motors that rotate between a lifting position and a thrusting position | US14626357 | 2015-02-19 | US09561849B2 | 2017-02-07 | Ricky Dean Welsh |
| This disclosure describes a configuration of an unmanned aerial vehicle (“UAV”) that will facilitate extended flight duration. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (also known as an octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a pivot assembly that may rotate about an axis from a lifting position to a thrusting position. The pivot assembly may include two or more offset motors that generate a differential force that will cause the pivot assembly to rotate between the lifting position and the thrusting position without the need for any additional motors or gears. | ||||||
| 34 | VEHICLE INCLUDING A TETRAHEDRAL BODY OR CHASSIS | US14631156 | 2015-02-25 | US20160376001A1 | 2016-12-29 | Robin Felix |
| A vehicle constructed in the shape of tetrahedral. The vehicle may be an aircraft, a space-craft, a sub-surface vehicle, or an unmanned drone. A tetrahedral body component is one of: a regular tetrahedron, an extended tetrahedron, a foreshortened tetrahedron, a tapered tetrahedron, and a truncated tetrahedron. A means for propulsion is mounted to at least one of the faces of the tetrahedral body component. The means for propulsion may include a turbine engine, a water jet, a gas jet, or electromagnetic propulsion. In another embodiment, the means for propulsion include an engine and a propeller. The engine block is mounted internal to the tetrahedral body component, and is located at the intersection of a tetrahedral shape with a cube shape. The engine block is mounted to the tetrahedral body component by struts perpendicular to the faces of the engine block. | ||||||
| 35 | ELECTRICALLY POWERED PERSONAL VEHICLE AND FLIGHT CONTROL METHOD | US15145342 | 2016-05-03 | US20160244156A1 | 2016-08-25 | Markus Leng |
| An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control. | ||||||
| 36 | Electrically powered aerial vehicles and flight control methods | US14046729 | 2013-10-04 | US09346542B2 | 2016-05-24 | Markus Leng |
| An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control. | ||||||
| 37 | AIRCRAFT | US14854380 | 2015-09-15 | US20160083075A1 | 2016-03-24 | Matthew MOXON |
| An aircraft (40). The aircraft comprises a plurality of propellers (46) mounted to wings (44). Each propeller comprises at least one blade (72, 74) coupled to a respective propeller cyclic actuator (78) configured to cyclically alter the pitch of the respective blade (72, 74) as the propeller rotates. The aircraft (40) is configured such that provision of cyclic pitch to the propeller (46) twists at least a portion of the wing (44) about a span of the wing (46) relative to the fuselage (42), to thereby adjust the local angle of incidence of the wing (46). | ||||||
| 38 | VANE ASSEMBLY FOR AN UNDUCTED THRUST PRODUCING SYSTEM | US14771975 | 2013-10-23 | US20160010487A1 | 2016-01-14 | Andrew BREEZE-STRINGFELLOW; Darek Tomasz ZATORSKI; Richard David CEDAR |
| A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle. | ||||||
| 39 | Screw conveyor shape propeller | US13005732 | 2011-01-13 | US08388391B1 | 2013-03-05 | Vladimir Vorobyev; Anait Serobyan |
| The present invention features a screw propeller system for use in a machine including a watercraft or an aircraft. The system features two or more screw propellers installed in the machine. Each screw propeller comprises an axle with a spiral blade disposed on the axle, and a tube hub. A differential and disc-brake device is operatively connected to each the first screw propeller and the second screw propeller. The differential and disc-brake device functions to steer the machine. | ||||||
| 40 | Variable pitch anti torque coaxial counter rotation bi-prop rotor | US11880431 | 2007-07-23 | US20090026310A1 | 2009-01-29 | Romeo S. Linn |
| Single engine aircrafts, spot light, seaplanes, ultra-light planes, gyro-planes, power parachutes, trikes, airship etc commonly use fixed pitch low efficiency propellers that generate unbalancing torque. Pilots need to make offset turning to anti-torque. The subject novel anti torque coaxial counter rotation Bi-Prop Rotor fill out the empty of such variable and reversible thrust anti-torque propulsion device. The Bi-Prop Rotor comprises an on axis driving compact unobvious gear box; 2 sets multiple blades prop-rotors with variable pitch push rods and bearing-plate assemblies, co-axial tandem mounted at both sides of the gear box; a set sliding bridge mechanism that synchronized the tandem prop-rotors blade pitch turning; and a driving pulley chain or bell driving system. When engine power up the driving pulley, the primary prop-rotor mounted with the pulley rotates, and drives the gear box. The gear box converts rotation to counter direction in the same RPM, and drives the second prop-rotor on axis end rotating. This bi-prop rotor has multiple unique features: A, anti-torque; B, linear vary blade pitch angle and thrust; C, can reverse blade pitch direction to produce reversed thrust to do air speed deceleration, or air braking; D, has extraordinary aerodynamic efficiency; E, substantially produces a lot more thrust with same engine power. | ||||||
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