| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 101 | VEHICLE CONFIGURATION WITH MOTORS THAT ROTATE BETWEEN A LIFTING POSITION AND A THRUSTING POSITION | US15381743 | 2016-12-16 | US20170101175A1 | 2017-04-13 | 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. | ||||||
| 102 | PROPULSION UNIT FOR AN AIRCRAFT | US15285117 | 2016-10-04 | US20170096231A1 | 2017-04-06 | Augustin Marc Michel Curlier |
| Propulsion unit for an aircraft, comprising a turbine, at least one propeller offset with respect to the turbine, and a power transmission disposed between the turbine and the propeller, the transmission comprising in series two constant velocity joints with a slide connection. | ||||||
| 103 | AIRFRAME-INTEGRATED PROPELLER-DRIVEN PROPULSION SYSTEMS | US14631423 | 2015-02-25 | US20160244150A1 | 2016-08-25 | Helio HIRANO; Luis Gustavo TRAPP |
| Propeller-driven craft (e.g., aircraft) are provided with at least one propulsion system having at least one engine and at least one aerial tractor propeller which generates a propeller propwash airflow when driven by the engine. At least one airfoil is disposed in the propeller propwash airflow of the at least one aerial tractor propeller. The airfoil is contoured and oriented relative to a swirl rotation angle (ω) of the propeller propwash airflow in order to induce a forward force component on the craft in response to the propeller propwash airflow over the at least one airfoil, thus improving the craft's performance and/or reducing fuel consumption. | ||||||
| 104 | Method For Controlling An Aircraft Propeller System During Thrust Reversal | US14934631 | 2015-11-06 | US20160121998A1 | 2016-05-05 | Miguel Angel Martin Moreno; Eva Carlon Ortiz; Manuel Silvestre Salas; Vincent Lamonzie |
| The present invention refers to a method for controlling an aircraft propeller system during thrust reversal, wherein it is checked whether each power plant is ready for the transition to negative pitch, and where the propellers transition to negative pitch is controlled from a flight control system, such as only when both power plants are ready for the transition to negative pitch, the flight control system instructs the aircraft propeller system to reverse thrust. If a power plant failure is detected before a reversal order is received, then the flight control system is informed of that failure condition, and then the flight control system will disable the thrust reversal operation as long as the failure condition remains. The method of the invention improves the aircraft controllability during landing operations, reduces pilot workload, and improves passenger comfort during landing and taxing. | ||||||
| 105 | PROPULSION SYSTEM FOR A HYBRID (CONVERTIBLE) VEHICLE | US14760572 | 2013-09-02 | US20150353189A1 | 2015-12-10 | Dmitry Nikolaevich KHARITONOV |
| The power plant of the hybrid (transformed) vehicle belongs to area of light aircrafts and motorcycles. The essence of the invention is a possibility of transfer the rotary moment from the motorcycle chain not only to the rear wheel, but also to two propellers. Thus propellers together with balancing device, called by the elements of the air drive (EAD) can be fixed in two positions. Firstly when the plane of their rotation is perpendicular to the planes of rotation of a back wheel (the flight mode). Secondly, when propellers (and EAD) are pressed to side parts of the hybrid aircraft (the land mode). | ||||||
| 106 | UNDUCTED THRUST PRODUCING SYSTEM ARCHITECTURE | US14438006 | 2013-10-23 | US20150291276A1 | 2015-10-15 | Darek Tomasz Zatorski; Jeffrey Hamel |
| An unducted thrust producing system has a rotating element with an axis of rotation and a stationary element. The rotating element includes a plurality of blades, and the stationary element has a plurality of vanes configured to impart a change in tangential velocity of the working fluid opposite to that imparted by the rotating element acted upon by the rotating element. The system includes an inlet forward of the rotating element and the stationary element. | ||||||
| 107 | UNDUCTED THRUST PRODUCING SYSTEM | US14437872 | 2013-10-23 | US20150284070A1 | 2015-10-08 | Andrew Breeze-Stringfellow; Syed Arif Khalid; Leroy Harrington Smith, JR. |
| An unducted thrust producing system has a rotating element with an axis of rotation and a stationary element. The rotating element includes a plurality of blades each having a blade root proximal to the axis, a blade tip remote from the axis, and a blade span measured between the blade root and the blade tip. The rotating element has a load distribution such that at any location between the blade root and 30% span the value of ΔRCu in the air stream is greater than or equal to 60% of the peak ΔRCu in the air stream. | ||||||
| 108 | PROPULSION SYSTEM FOR AIRCRAFT, IN PARTICULAR LIGHTWEIGHT AIRCRAFT | US14428654 | 2013-09-09 | US20150210380A1 | 2015-07-30 | Herwig Fischer; Hanno Fischer |
| A propulsion system for aircraft, in particular lightweight aircraft, provides a low-noise and low-cost aircraft. The propulsion system includes at least two ducted propellers (3, 3′). The ducts of are provided laterally on the fuselage (4) of the aircraft in such a way that the common net thrust of the ducted propellers is substantially collinear to the net drag. | ||||||
| 109 | CONTRA-ROTATING OPEN FAN PROPULSION SYSTEM | US14032163 | 2013-09-19 | US20150078888A1 | 2015-03-19 | Sina S. Golshany; David Miles Huntly; Adriana W. Blom; Todd R. Erickson; Paul R. Tretow |
| In one aspect a propulsion system comprises an engine and a drive assembly coupled to the engine, comprising a first driveshaft rotatable in a first direction about a first axis, a first fan coupled to the first driveshaft to rotate in the first direction, and a clutch assembly to selectively disengage the first fan from the first driveshaft. Other aspects may be described. | ||||||
| 110 | Propulsion linearizing mechanism | US10485208 | 2002-08-06 | US06988868B2 | 2006-01-24 | Eric Ashworth |
| A propulsion linearizing mechanism is provided for linearizing a fluid flow. The mechanism includes a frame having a cylindrical outer baffle which rotatably supports a plurality of propeller elements thereon. Each propeller element defines a respective sweep area as the propeller element is rotated which overlaps sweep areas of adjacent propeller elements. The outer baffle circumscribes an outer periphery of the collective sweep areas of the respective propeller elements. The propeller elements rotate in the same direction whereby forces of curvature flow of adjacent propeller elements substantially cancel one another to linearize fluid flow through the mechanism. Additional baffles and infills within the areas of non blade sweep may be provided for particular applications of the mechanism. In various applications, linear forces of vector flow are formed by integrating curvature forces of tangential flow and economy flow systems are established to increase force potentials on the planes of rotating propellers to provide the emission and induction flow with an insulation whereby fluid in the immediate vicinity of the mobile flow remains in an undisturbed static state. This allows a fluid propulsion assembly to be fitted with an outer utility mantle in the static zone of the field. | ||||||
| 111 | Fluid flow control mechanism | US10485208 | 2004-07-21 | US20040240998A1 | 2004-12-02 | Eric Ashworth |
| A fluid flow control mechanism is provided for linearizing a fluid flow. The mechanism includes a frame having a cylindrical outer baffle which rotatably supports a plurality of propeller elements thereon. Each propeller element defines a respective sweep area as the propeller element is rotated which overlaps sweep areas of adjacent propeller elements. The outer baffle circumscribes an outer periphery of the collective sweeps areas of the respective propeller elements. The propeller elements rotate in the same direction whereby forces of curvature flow of adjacent propeller elements substantially cancel one another to linearize fluid flow through the mechanism. Additional baffles and infills within the areas of non blade sweeps may be provided for particular applications of the mechanism. In various applications, linear forces of vector flow are formed by integrating curvature forces of tangential flow and economy flow systems are formed by integrating curvature forces potentials on the planes of rotating propellers to provide the emission and induction flow with an insulation whereby fluid in the immediate vicinity of the mobile flow remains in an undisturbed static state. This allows a fluid propulsion assembly to be fitted with an outer utility mantle in the static zone of the field. | ||||||
| 112 | High velocity propeller | US934188 | 1997-09-19 | US5810289A | 1998-09-22 | William F. Sager |
| A propeller for fluid propulsion comprises a pair of substantially rigid blades which rotate about their longest dimension in opposite directions, the blades each being oppositely helically twisted along the longest blade dimension and positioned together in synchronously opposite, rotatable condition, with the rotating blades passing by each other in closely spaced relation substantially without physical contact. The blades occupy a tubular housing enclosing the rotating blades in closely-spaced relation between the housing and blades. Further sealing is provided by each blade side carrying a hemicylindrical wall with a concave side facing outwardly, each hemicylindrical wall being helically twisted in a manner identical to the helical twist of the blade. The hemicylindrical walls have a cross-sectional diameter that permits, upon blade rotation, an edge of the other blade to sweep across the concave side of each hemicylindrical wall in closely spaced relation for sealing purposes. | ||||||
| 113 | Control system for interconnected propellers | US21225662 | 1962-07-25 | US3107881A | 1963-10-22 | STUART III JOSEPH |
| 114 | 수직이착륙항공기 및 그 천이방법 | KR1020170024467 | 2017-02-24 | KR1020180097826A | 2018-09-03 | 장진한; 김도현 |
| 수직이착륙항공기및 그천이방법이개시된다. 수직이착륙항공기는, 전방날개부및 후방날개부를포함하는비행동체, 상기전방날개부의좌측날개부와우측날개부에각각마련되는다수의틸팅프로펠러, 상기후방날개부에마련되는다수의틸팅프로펠러및 상기전방날개부와상기후방날개부의프로펠러동작을독립적으로제어하는제어부를포함한다. | ||||||
| 115 | 적어도 2개의 로터 조립체와 보호판이 있는 추력 생성 유닛 | KR1020180010073 | 2018-01-26 | KR1020180088315A | 2018-08-03 | |
| 본발명은미리결정된방향(23)으로추력을생성하기위한추력생성유닛(3d)에관한것으로, 보호판(6d)과적어도 2개의로터조립체(7d,8d)를포함하고, 보호판(6d)은내부볼륨(20c)을정의하고, 적어도 2개의로터조립체(7d,8d) 중제1 로터조립체(7d)는제1 로터축을정의하며, 적어도 2개의로터조립체(7d,8d) 중제2 로터조립체(8d)는제2 로터축을정의하고, 제1 및제2 로터축(12d)은 (ⅰ) 축이같게배치되고, (ⅱ) 미리결정된방향(23)에대해연관된경사각(21a,22a)만큼경사져있으며, 상기연관된경사각(21a,22a)은 -60°와 +60°사이의범위에포함되어있고바람직하게는 0°이며, 상기제1 로터조립체(7d)는상기보호판(6d)의내부볼륨(20c)의바깥쪽에배치된다. | ||||||
| 116 | 프로펠러 사이 간격을 조절할 수 있는 멀티콥터 | KR1020160051666 | 2016-04-27 | KR1020170122903A | 2017-11-07 | 김훈모; 조성식; 송부천; 김현우; 최익수; 홍석범 |
| 본발명은프로펠러사이간격을조절할수 있는멀티콥터에관한것으로서, 본발명에따른프로펠러사이간격을조절할수 있는멀티콥터는몸체부;와, 다수마련되어상기몸체부의비행을위한양력을제공하는양력발생부;와, 상기몸체부와양력발생부를연결하는연결부; 및상기연결부의길이를신축하는신축부;를포함하는것을특징으로한다. 이에의하여, 가로와세로중 적어도어느하나의폭이조절되도록함으로써, 비행중 장애물구간의통과가용이한것은물론보관공간을최소화할수 있는프로펠러사이간격을조절할수 있는멀티콥터가제공된다. | ||||||
| 117 | 다목적용 멀티로터 드론 | KR1020160184116 | 2016-12-30 | KR101764271B1 | 2017-08-04 | 서이환 |
| 본발명은비행몸체와, 상기비행몸체의외측면에방사형으로연결되어있는복수개의지지프레임과, 상기지지프레임에장착되어제자리서회전하는로터와, 상기로터에체결되어로터와함께회전하는프로펠러와, 상기로터가회전하도록동력을부여하는배터리와, 상기비행몸체가지면에착륙시지면으로부터지지하는랜딩기어로이루어진다목적용멀티로터드론에관한것으로서, 더욱상세하게는상기랜딩기어는비행몸체에수평상태로체결되는제1관절체와, 상기제1관절체에끝단부가지면에접촉되도록체결되는제2관절체로이루어지는것으로, 상기제2관절체는제1관절체에상하로회동하도록힌지결합되어있되, 상기제1관절체와제2관절체사이에는제2관절체를회동시킨후, 제2관절체를고정하는고정부재가장착되어있으며, 상기랜딩기어(120)를상하로반전시켜상하로반전된랜딩기어(120)가지면에지지되도록하면, 프로펠러(150)로부터발생하는양력이랜딩기어(120)를따라지면을향하도록로터(140)에체결되어있는프로펠러(150)도상하면을반전시켜로터(140)에장착하는것이특징인다목적용멀티로터드론에관한것이다.따라서, 본발명은랜딩기어및 프로펠러를손쉽게반전시킬수 있어, 드론의임무즉, 사용목적에구애를받지않고사용할수 있으며, 이로인해별도의드론을구입하지않아도되기때문에비용절감의현저한효과도있다. | ||||||
| 118 | 이동 장치 | KR1020160002774 | 2016-01-08 | KR1020170083380A | 2017-07-18 | 정창현; 송일영 |
| 본발명의일 측면에따르면, 본체와, 회동이가능하도록상기본체에설치되는적어도하나의회동비행장치와, 상기본체의아래쪽으로연장되는적어도하나의가이드부와, 상기가이드부를따라움직일수 있도록설치되는움직임부와, 상기움직임부의움직임에의해상기회동비행장치를회동시켜추진력의방향을변경시키는작용부를포함하는이동장치를제공한다. | ||||||
| 119 | 접이식 날개를 갖는 드론 | KR1020160039578 | 2016-03-31 | KR101713669B1 | 2017-03-08 | 차현록; 박봉기 |
| 본발명은접이식날개를갖는드론에관한것으로, 보다상세하게는부피가최소화되어운송이용이한접이식날개를갖는드론에관한것이다. 본발명의일실시예는접이식날개를갖는드론에있어서, 본체부; 및상기본체부에결합되는복수의날개부를포함하며, 상기날개부는전방으로회동시제1 위치에고정되고, 후방으로회동시제2 위치에고정되도록마련되는것을특징으로하는것인접이식날개를갖는드론을제공한다. 또한, 본발명의일실시예는접이식날개를갖는드론에있어서, 본체부; 및상기본체부에결합되는제1 날개유닛과, 상기제1 날개유닛의양측면으로연장된한 쌍의제2 날개유닛을갖는한 쌍의날개부를포함하며, 상기제1 날개유닛은전방으로회동시제1 위치에고정되고, 후방으로회동시제2 위치에고정되며, 상기제2 날개유닛은전방으로회동시제5 위치에고정되고, 후방으로회동시제6 위치에고정되는것을특징으로하는것인접이식날개를갖는드론을제공한다. | ||||||
| 120 | 3-팬 방식 수직이착륙 항공기 | KR1020010080113 | 2001-12-17 | KR1020030049796A | 2003-06-25 | 최성욱; 이장연 |
| PURPOSE: A vertical taking-off/landing airplane is provided to increase the propelling efficiency by forming a fan blade in a duct shape to shield the structure of a ring. CONSTITUTION: In a vertical taking-off/landing of an airplane, two main lift fans(1,2) to be tilted and a fixing type front lift fan(3) to be installed in the front part of the airplane are driven. In a forward flying, the driving of the front lift fan is isolated and two main lift fans are driven by tilting. Thereby, the vertical taking-off and the landing are efficient and the high forward flying speed is obtained. | ||||||
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