| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | High velocity propeller | US492819 | 1995-06-20 | US5810288A | 1998-09-22 | William F. Sager |
| A propeller for fluid propulsion (such as air or water) comprises a pair of substantially rigid blades. The blades are mounted for rotation about respective, separate, parallel rotation axes, with the axes being also substantially parallel to the longest dimension of the blades. The blades each define a plate that is oppositely helically twisted along the longest blade dimension compared with the other blade. The blades are positioned together in synchronously opposite, rotatable condition, with the rotating blades passing by each other in closely spaced relation without physical contact. A tubular housing encloses the rotating blades in closely-spaced relation between the housing and blades. Such a blade system can provide a high velocity jet of large mass at relatively low rotational speed. | ||||||
| 42 | Propeller control system | US12085761 | 1961-06-02 | US3112901A | 1963-12-03 | KOHMAN WAYNE E |
| 43 | 지면 이동 및 자력 상승 가능한 드론 | KR1020150177185 | 2015-12-11 | KR101807082B1 | 2017-12-08 | 곽승계 |
| 본발명은, 구름부재를구비하는메인프레임; 상기메인프레임에스윙가능하게설치되는서브프레임; 상기서브프레임에설치되는로터; 및상기로터의회전방향이달라지도록상기로터에공급되는전류의극성을변환하여, 상기구름부재가지면에의해구르게하거나, 상기구름부재가지면위로상승하게하는제어유닛을포함하는, 지면이동및 자력상승가능한드론을제공한다. | ||||||
| 44 | 지면 이동 및 자력 상승 가능한 드론 | KR1020150177185 | 2015-12-11 | KR1020170069679A | 2017-06-21 | 곽승계 |
| 본발명은, 구름부재를구비하는메인프레임; 상기메인프레임에스윙가능하게설치되는서브프레임; 상기서브프레임에설치되는로터; 및상기로터의회전방향이달라지도록상기로터에공급되는전류의극성을변환하여, 상기구름부재가지면에의해구르게하거나, 상기구름부재가지면위로상승하게하는제어유닛을포함하는, 지면이동및 자력상승가능한드론을제공한다. | ||||||
| 45 | 수직 이륙 항공기 | KR1020157005114 | 2013-07-19 | KR1020150038447A | 2015-04-08 | 헤셀바르트,요나탄 |
| 본발명은날개가있는수직이륙항공기(1)에관한것이다. 제1 구동유닛(4)과제2 구동유닛(5)가날개(3)에선회가능하게장착된다. 상기제1 구동유닛(4)과제2 구동유닛(5)은날개(3)의끝단(12)으로부터거리를두고날개(3) 상에배치된다. 상기항공기(1)의종축(10)으로부터상기제1 구동유닛(4)까지의제1 거리는상기항공기(1)의종축(10)으로부터상기제2 구동유닛(5)까지의제2 거리와거의동일하다. 상기제1 구동유닛(4)과제2 구동유닛(5)은수평비행위치와수직비행위치로회동가능하다. 수평비행위치에서상기제1 구동유닛(4)은날개면 위에서, 상기제2 구동유닛(5)은상기날개면 아래에서, 상기날개상에배치된다. 수직비행위치에서상기제1 구동유닛(4)과제2 구동유닛(5)은대략하나의수평면에배치된다. 상기제1 구동유닛(4)과제2 구동유닛(5)은각각회동아암(7)을가지고, 상기회동아암(7)은상기날개(3)에회동가능하게장착된다. | ||||||
| 46 | VTOL AIRCRAFT WITH STEP-UP OVERLAPPING PROPELLERS | US16354768 | 2019-03-15 | US20190233098A1 | 2019-08-01 | Yu Tian |
| A vertical takeoff and landing (VTOL) fixed-wing aircraft having overlapping propellers and low handing vertical stabilizers disposed on the rear end of the aircraft. | ||||||
| 47 | Aircraft with linear thruster arrangement | US15861479 | 2018-01-03 | US20180354609A1 | 2018-12-13 | Joseph R. Renteria |
| A linear thruster aircraft includes, an aircraft body; an air craft control unit with a processor, a non-transitory memory, and an input/output component; and at least one linear thruster arrangement with at least four thrusters mounted along at least one elongated axis of the aircraft body, such that the thrusters are configured to provide lift, pitch, roll, and yaw movement. Optionally, the linear thruster arrangement can include an alternating lateral offset of the thrusters from the elongated axis. | ||||||
| 48 | ELECTRICALLY POWERED AERIAL VEHICLES AND FLIGHT CONTROL METHODS | US16027848 | 2018-07-05 | US20180312248A1 | 2018-11-01 | 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. | ||||||
| 49 | SIX DEGREE OF FREEDOM AERIAL VEHICLE WITH A RING WING | US15435121 | 2017-02-16 | US20180229839A1 | 2018-08-16 | Gur Kimchi; Louis LeRoi LeGrand, III; Dominic Timothy Shiosaki; Ricky Dean Welsh |
| Described is an apparatus and method of an aerial vehicle, such as an unmanned aerial vehicle (“UAV”) that can operate in either a vertical takeoff and landing (VTOL) orientation or a horizontal flight orientation. The aerial vehicle includes a plurality of propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll) when in the VTOL orientation. The aerial vehicle also includes a ring wing that surrounds the propulsion mechanisms and provides lift to the aerial vehicle when the aerial vehicle is operating in the horizontal flight orientation. | ||||||
| 50 | Tiltwing multicopter with foldable and non-foldable propellers | US15801052 | 2017-11-01 | US09975631B1 | 2018-05-22 | Campbell McLaren; Damon Vander Lind; Pranay Sinha; Thomas Van Alsenoy |
| An aircraft includes a front tiltwing which in turn includes two non-foldable outer propellers and four foldable inner propellers. The four foldable inner propellers are rotating at least some of the time while the front tiltwing is held in a vertical takeoff and landing position. The four foldable inner propellers are stowed at least some of the time while the front tiltwing is held in a forward flight position. The aircraft also includes a back tiltwing which includes two non-foldable back propellers. | ||||||
| 51 | Multicopter propeller guard system | US15175289 | 2016-06-07 | US09975624B1 | 2018-05-22 | William B. Harvey |
| The embodiments relate to an apparatus for controlling the angular position of propeller guards of a multicopter. The apparatus includes a chassis having at least three sides, including first and second sides meeting at a first vertex and second and third sides meeting at a second vertex. Each side is in communication with at least one propeller. At least one guard is in communication with the chassis. Each guard corresponds to a respective side, and each guard has oppositely disposed first and second terminals. The apparatus further includes a rotation mechanism in communication with the at least one guard to control an angular position of at least one guard relative to the chassis. The angular position is controlled in real time to mitigate damage with regard to an approaching or potential obstacle. | ||||||
| 52 | Airframe-integrated propeller-driven propulsion systems | US14631423 | 2015-02-25 | US09914528B2 | 2018-03-13 | 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. | ||||||
| 53 | Propulsion system for aircraft, in particular lightweight aircraft | US14428654 | 2013-09-09 | US09908613B2 | 2018-03-06 | 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. | ||||||
| 54 | BISTABLE PITCH PROPELLER SYSTEM WITH UNIDIRECTIONAL PROPELLER ROTATION | US15225028 | 2016-08-01 | US20180029694A1 | 2018-02-01 | Damon Vander Lind; Todd Reichert |
| A propeller includes a blade free to rotate about a longitudinal axis of the blade. The propeller also includes a mechanical stop positioned to engage mechanically a first portion of the blade and/or a first structure coupled mechanically to the blade when the blade is in a first position. The propeller also includes a magnetic stop positioned to engage magnetically a second portion of the blade and/or a second structure coupled mechanically to the blade when the blade is in a second position. The blade rotates to the first position against the mechanical stop when the propeller is rotated at a first rotational speed and the blade rotates to the second position against the magnetic stop when the propeller is rotated at a second rotational speed in a same direction as when the blade is in the first position. | ||||||
| 55 | Aircraft with Independently Controllable Propulsion Assemblies | US15200182 | 2016-07-01 | US20180002012A1 | 2018-01-04 | John Richard McCullough; Paul K. Oldroyd |
| In some embodiments, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, a flight control system operably associated with the distributed propulsion system and a pod assembly selectively attachable to the flying frame. The distributed propulsion system includes a plurality of propulsion assemblies that are independently controlled by the flight control system, thereby enabling the flying frame to have a vertical takeoff and landing mode and a forward flight mode. | ||||||
| 56 | A novel crash-resistant aircraft and crash-resistant control method | US15516035 | 2015-09-09 | US20170305563A1 | 2017-10-26 | Guoxin WEI |
| A novel crash-resistant aircraft includes a fuselage and an aircraft base connected together via a movable fastener, and said fuselage comprises a cockpit, a cabin and an empennage. The aircraft base comprises a belly hold cargo bay, a fuel tank, an undercarriage, a power unit and wings. The empennage is also connected to the tail end of said fuselage via a movable fastener. A crash-resistant propeller system capable of bringing said fuselage upward is set up at the top of said cabin, a crash-resistant recoil devices set up beneath said cabin. The crash-resistant aircraft also comprises a control system disposed in said cockpit, and when said aircraft is in an accident in midair, said control system releases said movable fastener to abandon said aircraft base and said empennage. Also disclosed is a crash-resistant operation method of the crash-resistant aircraft. | ||||||
| 57 | Method for controlling an aircraft propeller system during thrust reversal | US14934631 | 2015-11-06 | US09623958B2 | 2017-04-18 | 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. | ||||||
| 58 | Method for controlling an aircraft in the form of a multicopter and corresponding control system | US14402843 | 2013-05-17 | US09618939B2 | 2017-04-11 | Stephan Wolf; Thomas Ruf |
| A method and a system are provided for controlling an aircraft in the form of a multicopter which has a plurality of redundant rotors (4), preferably arranged in a common rotor plane, in order, on the one hand, to generate lift, and, on the other hand, also propulsion by inclining the at least one rotor plane, wherein the regulation of the position and the control of the multicopter are carried out by changing rotor rotational speeds as a function of pilot control instructions. The system is characterized in that the rotors (4) are connected to one another in terms of data technology via a failsafe network (8), and they communicate their respective operating state, in particular their rotor rotational speed, in the network (8), and in that the network contains a first multiplicity of redundant sensors which determine control-relevant data and make it available in the network, in particular inclination, acceleration, rotational speed and/or position in all three spatial axes of the multicopter. | ||||||
| 59 | Gyroscopic Orbiter with Vertical Takeoff and Vertical Landing Capabilities | US15184186 | 2016-06-16 | US20170088291A1 | 2017-03-30 | Thomas Norman Hesse |
| A gyroscopic orbiter with vertical takeoff and vertical landing capabilities can transition between different functional modes while in-flight. The orbiter typically includes a fuselage, a front boom, a front propulsion unit, a rear boom, and a rear propulsion unit. The front boom is mounted at two pivot points to a bow of the fuselage by the front boom. The rear boom is mounted at two pivot points to a stern of the fuselage by the rear boom. One functional mode is the vertical takeoff and landing mode, wherein the propulsion units are oriented parallel to each other and are directed upward. Another functional mode is the shuttle mode, wherein the propulsion units are oriented at an angle with each other, and the front propulsion unit is directed forward. Another functional mode is the high speed mode, wherein the propulsion units are oriented collinear with a roll axis of the fuselage. | ||||||
| 60 | VEHICLE CONFIGURATION WITH MOTORS THAT ROTATE BETWEEN A LIFTING POSITION AND A THRUSTING POSITION | US14626357 | 2015-02-19 | US20160244157A1 | 2016-08-25 | 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. | ||||||
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