| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | METHOD FOR CONTROLLING AN AIRCRAFT IN THE FORM OF A MULTICOPTER AND CORRESPONDING CONTROL SYSTEM | US14402843 | 2013-05-17 | US20150212523A1 | 2015-07-30 | 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. | ||||||
| 62 | VERTICAL-TAKEOFF AIRCRAFT | US14416760 | 2013-07-19 | US20150175260A1 | 2015-06-25 | Jonathan Hesselbarth |
| A vertical-takeoff aircraft with a wing. A first drive unit and a second drive unit are swivellably mounted on the wing. The first drive unit and the second drive unit are arranged on the wing at a distance from a wing-end of the wing. A first distance between the first drive unit and a longitudinal axis of the aircraft is approximately equal to a second distance between the second drive unit and the longitudinal axis of the aircraft. The first drive unit and the second drive unit are swivellable into a horizontal flying position and a vertical flying position. In the horizontal flying position the first drive unit is arranged above a wing surface and the second drive unit below the wing surface on the wing. In the vertical flying position the first drive unit and the second drive unit are arranged in an approximately horizontal plane. The first drive unit and the second drive unit each have a swivel arm, wherein the swivel arms are swivellably mounted on the wing. | ||||||
| 63 | ELECTRICALLY POWERED AERIAL VEHICLES AND FLIGHT CONTROL METHODS | US14046729 | 2013-10-04 | US20140097290A1 | 2014-04-10 | 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. | ||||||
| 64 | AIRCRAFT WITH AT LEAST TWO PROPELLER DRIVES ARRANGED AT A DISTANCE FROM ONE ANOTHER IN THE SPAN WIDTH DIRECTION OF THE WINGS | US13003501 | 2009-07-13 | US20110186679A1 | 2011-08-04 | Daniel Reckzeh |
| An aircraft with a fuselage and two aerodynamic wings, which each accommodate at least two propeller drives spaced a apart from each other in the wingspan direction, each with a propeller rotational axis, wherein the aircraft has a controller for activating the propeller drives, wherein in one operating mode of the controller for generating propulsion, the propeller drives are activated in such a way that the outer section of a propeller secured to the respective propeller rotational axis is moved from the top down on the side facing the fuselage. | ||||||
| 65 | Aircraft propulsion system and method | US10091273 | 2002-03-05 | US20030168552A1 | 2003-09-11 | Paul Anthony Brown |
| The invention concerns an aircraft propulsion system involving propellers, where two propellers are overlapped partially and staggered so that they do not strike each other in a complete range of motion. Two engines that are mounted on to the same fuselage power each propeller. | ||||||
| 66 | Traversing blade-rotary propeller | US460032 | 1983-03-28 | US4509899A | 1985-04-09 | Larry J. Frederick |
| A traversing blade rotary propeller useful as a propulsion system for various types of boats and aircraft or as a wind or water actuated turbine. A traversing blade rotary propeller of this type includes a stationary main shaft, a mount to which an end of the stationary main shaft is affixed, a central housing structured to carry a pair of alternately disposed, perpendicularly projecting radial arm shafts, and where the device is used as a propulsion system, power means for rotation of said central housing relative to the fixed axis formed by said stationary main shaft. A pair of propeller shafts extend perpendicularly from an end of each of said radial arm shafts, and flat propeller blades are attached to each. The inboard ends of each of the radial arm shafts are operatively engaged with the stationary main shaft, and the outboard ends are operatively engaged with the propeller shafts, as via gears such that rotation of the central housing produces rotation of the propeller shafts. The propeller shafts are mounted perpendicular to the radial arm shafts, and equally and oppositely deflected at an angle relative to a line passing parallel to the axes of the radial arms to perpendicularly intersect the stationary main shaft. During rotation the propeller blades maintain a fixed vertical (or horizontal) orientation while the outwardly faced edges thereof oscillate in equal and opposite directions, one counterbalancing the other, across the swath defined by the circle made by the path defined by the outer terminal ends of the radial arms which revolve about the stationary main shaft. | ||||||
| 67 | Thrust augmenting device for jet aircraft | US37778473 | 1973-07-09 | US3811791A | 1974-05-21 | COTTON R |
| A dual set of counter-rotating impulse turbine wheels having short propeller blades about their periphery are disposed in the exhaust emitted by a jet engine to augment its thrust at lower subsonic speeds by extracting energy from the high velocity gases. The counter rotation minimizes torque loads. The turbine wheels may be closely mounted behind the engine and directly connected thereto or movably mounted for optional retraction out of the path of the exhaust at higher speeds when the jet engine is more efficient.
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| 68 | Propeller drives | US23146551 | 1951-06-14 | US2826255A | 1958-03-11 | PETERSON VICTOR W |
| 69 | Air turbine | US74228124 | 1924-10-08 | US1578818A | 1926-03-30 | FITZGERALD JAMES J |
| 70 | AIRCRAFT | EP15185159.9 | 2015-09-15 | EP3000722B1 | 2018-12-26 | Moxon, Matthew |
| 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). | ||||||
| 71 | A THRUST PRODUCING UNIT WITH AT LEAST TWO ROTOR ASSEMBLIES AND A SHROUDING | EP17400003.4 | 2017-01-26 | EP3354559A1 | 2018-08-01 | Mores, Sebastian; Kiesewetter, Uwe; Bebesel, Marius |
The invention is related to a thrust producing unit 3d for producing thrust in a predetermined direction 23, comprising a shrouding 6d and at least two rotor assemblies 7d, 8d, wherein the shrouding 6d defines an internal volume 20c, and wherein a first rotor assembly 7d of the at least two rotor assemblies 7d, 8d defines a first rotor axis and a second rotor assembly 8d of the at least two rotor assemblies 8d defines a second rotor axis, the first and second rotor axes 12d being one of: (i) coaxially arranged, and (ii) inclined by associated inclination angles 21a, 22a with respect to the predetermined direction 23, the associated inclination angles 21a, 22a being comprised in a range between -60° and +60°, and preferably amounting to 0°, and wherein the first rotor assembly 7d is arranged outside of the internal volume 20c of the shrouding 6d.
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| 72 | AIRCRAFT HAVING A VERSATILE PROPULSION SYSTEM | EP17179010.8 | 2017-06-30 | EP3263456A1 | 2018-01-03 | OLDROYD, Paul K; McCULLOUGH, John Richard |
An aircraft (10) having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft (10) includes an airframe (12) and a versatile propulsion system attached to the airframe (12). The versatile propulsion system includes a plurality of propulsion assemblies (26a-d). A flight control system (40) is operable to independently control the propulsion assemblies (26a-d). The propulsion assemblies (26a-d) are interchangeably attachable to the airframe (12) such that the aircraft (10) has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies (26a-d) from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies (26a-d) from an electric power source.
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| 73 | VANE ASSEMBLY FOR AN UNDUCTED THRUST PRODUCING SYSTEM | EP13786820.4 | 2013-10-23 | EP2948633A1 | 2015-12-02 | BREEZE-STRINGFELLOW, Andrew; ZATORSKI, Darek, Tomasz; CEDAR, Richard, David |
| 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. | ||||||
| 74 | UNDUCTED THRUST PRODUCING SYSTEM ARCHITECTURE | PCT/US2013066392 | 2013-10-23 | WO2014066508A3 | 2014-07-17 | ZATORSKI DAREK TOMASZ; HAMEL JEFFREY ANTHONY |
| 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. | ||||||
| 75 | METHOD FOR CONTROLLING AN AIRCRAFT IN THE FORM OF A MULTICOPTER AND CORRESPONDING CONTROL SYSTEM | PCT/EP2013060267 | 2013-05-17 | WO2013174751A3 | 2014-01-16 | WOLF STEPHAN; RUF THOMAS |
| A method and a system are proposed 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. | ||||||
| 76 | SYSTEMS AND METHODS FOR ACOUSTIC RADIATION CONTROL | EP18169650.1 | 2018-04-26 | EP3401216A1 | 2018-11-14 | KEARNEY-FISCHER, Martin |
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.
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| 77 | AIRFRAME-INTEGRATED PROPELLER-DRIVEN PROPULSION SYSTEMS | EP16710084.1 | 2016-02-19 | EP3261923A1 | 2018-01-03 | HIRANO, Helio; TRAPP, Luis Gustavo |
| 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. | ||||||
| 78 | DRONE COMPORTANT DES AILES PORTANTES | EP17176471.5 | 2017-06-16 | EP3260370A1 | 2017-12-27 | LAVAGEN, Gauthier; MARI-MARI, Marc; BENATAR, Yoni; BARSE, Thomas |
L'invention concerne un drone à voilure tournante (10) comprenant un corps de drone (12) comprenant une carte électronique contrôlant le pilotage du drone, quatre bras de liaison (16) comprenant fixé solidairement un bloc propulseur (14). Les bras de liaison (16) forment des ailes portantes.
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| 79 | ELECTRICALLY POWERED AERIAL VEHICLES AND FLIGHT CONTROL METHODS | EP13843351 | 2013-10-04 | EP2903895A4 | 2016-06-01 | LENG MARCUS |
| 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. | ||||||
| 80 | Method for controlling an aircraft propeller system during thrust reversal | EP14382443.1 | 2014-11-07 | EP3018054A1 | 2016-05-11 | Martin Moreno, Miguel, Ángel; Carlón Ortiz, Eva; Silvestre Salas, Manuel; Lamonzie, Vincent |
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 propeller transition to negative pitch is controlled from a flight control system such that, 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 thrust reverse order is received, then the flight control system is informed of that failure condition, and then the flight control system will disable the thrust reverse operation as long as the failure condition remains. The method of the invention improves the aircraft controllability during landing operations, reduce pilots workload, and to improve passengers comfort during landing and taxing.
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