公开(公告)号：US20180305004A1

公开(公告)日：2018-10-25

申请号：US15576799

申请日：2016-05-25

Applicant: DOTTEREL TECHNOLOGIES LIMITED

Inventor： Samuel Seamus ROWE ,  Shuan Taggart Pentecost

IPC: B64C27/20 ,  B64C39/02

CPC classification number: B64C27/20 ,  B64C27/08 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2220/00

Abstract: A shroud for an aircraft having a noise reducing material on or in an inner surface of the shroud adjacent to one or more tips of the propeller. The noise reducing material is preferably an electrospun nanomaterial, particularly a ridged composite acoustic nanofibre. The interior surface of the shroud may be provided with a plurality of sound deflectors configured to dissipate sound by reflection and refraction, and absorb sound into the shroud body. The sound deflectors may be ribs or arrangements of discrete reflector elements.

公开(公告)号：US10046853B2

公开(公告)日：2018-08-14

申请号：US14827614

申请日：2015-08-17

Applicant: Aergility LLC

Inventor： James E. Vander Mey

IPC: B64C27/08 ,  B64C27/02 ,  B64C27/20 ,  B64C37/00 ,  B64C27/54 ,  B64D45/00 ,  B64C27/22 ,  B64C27/82 ,  B64D27/02

CPC classification number: B64C27/08 ,  B64C27/02 ,  B64C27/20 ,  B64C37/00 ,  B64C2027/8236 ,  B64D2027/026 ,  Y02T50/64

Abstract: An aircraft includes at least one propulsion engine, coupled to a fuselage, and configured to provide forward thrust to propel the aircraft along a first vector during forward flight. Each of at least two of multiple rotors coupled to the fuselage is coupled to a motor configured to supply power to that rotor and/or to draw power from that rotor. At least two of the rotors are configured to operate during forward flight to provide at least some lift to the aircraft along a second vector. A flight control system is configured to control the rotors that are configured to operate during forward flight in a power managed regime in which a net electrical power, consisting of the sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system.

公开(公告)号：US20180215465A1

公开(公告)日：2018-08-02

申请号：US15884238

申请日：2018-01-30

Applicant: Joseph Raymond Renteria

Inventor： Joseph Raymond Renteria

IPC: B64C29/00 ,  B64C25/10 ,  B64C27/02 ,  B64C27/26 ,  B64C27/28

CPC classification number: B64C29/0033 ,  B64C25/10 ,  B64C27/02 ,  B64C27/04 ,  B64C27/20 ,  B64C27/26 ,  B64C27/28 ,  B64C29/0025 ,  Y02T50/44

Abstract: A rotatable thruster aircraft includes a fixed wing; rotatable thruster assemblies, each including first and second thrusters that provide rotation via differential thrust; and vertical lift thrusters, optionally connected via an elongated member; and an aircraft control unit, including a processor, a non-transitory memory, an input/output component, and a power manager that controls specific power applied to the thrusters.

公开(公告)号：US10017245B2

公开(公告)日：2018-07-10

申请号：US15098221

申请日：2016-04-13

Applicant: David Geise ,  John Geise

Inventor： David Geise ,  John Geise

IPC: B64C27/08 ,  B64C27/20 ,  B64C1/06 ,  B64C27/14 ,  B64C27/52 ,  B64F5/10

CPC classification number: B64C27/08 ,  B64C1/061 ,  B64C27/14 ,  B64C27/20 ,  B64C27/52 ,  B64F5/10

Abstract: A multirotor flying vehicle including at least one rotor support frame organized on a geometric grid, with a plurality of rotor assemblies coupled to the at least one rotor support frame. At least one power supply is coupled to and powers the rotor assemblies. A control system is coupled to the rotor assemblies and is configured to operate the vehicle.

公开(公告)号：US20180170511A1

公开(公告)日：2018-06-21

申请号：US15831936

申请日：2017-12-05

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

Inventor： Sebastian MORES ,  Martin BLACHA ,  Christian REICHENSPERGER ,  Klaus RITTEL ,  Marco SCHNEEBERGER ,  Michael GEISS ,  Markus PASCHEK ,  Marius BEBESEL

IPC: B64C1/06 ,  B64D9/00 ,  B64D33/08 ,  B64D27/24

CPC classification number: B64C1/068 ,  B64C1/06 ,  B64C1/16 ,  B64C27/04 ,  B64C27/08 ,  B64C27/20 ,  B64C2201/024 ,  B64C2201/042 ,  B64D9/00 ,  B64D27/24 ,  B64D33/08 ,  Y02T50/44 ,  Y02T50/64

Abstract: An aircraft with a modular airframe. The modular airframe has a load carrying framework and at least one exchangeable covering item that exhibits a first predetermined shaping. The at least one exchangeable covering item is detachably mounted to the load carrying framework. The modular airframe is customizable by exchanging the at least one exchangeable covering item with a substitute exchangeable covering item that exhibits a second predetermined shaping.

公开(公告)号：US20180155016A1

公开(公告)日：2018-06-07

申请号：US15578452

申请日：2016-07-15

Applicant: Yuneec Technology Co., Limited

Inventor： Yu TIAN ,  Wenyan JIANG

IPC: B64C27/20 ,  B64C27/08 ,  B64D47/08 ,  B64C27/12 ,  B64C25/04 ,  B64C25/32

CPC classification number: B64C27/20 ,  B64C11/001 ,  B64C25/04 ,  B64C25/32 ,  B64C27/08 ,  B64C27/12 ,  B64C29/0025 ,  B64C39/024 ,  B64C2025/325 ,  B64C2201/027 ,  B64C2201/108 ,  B64D47/08

Abstract: Disclosed is an aerial vehicle, comprising: an airframe, a propeller(s), a duct(s) and a driving device, wherein the duct(s) is arranged on the airframe and adapted to increase a lifting force for the aerial vehicle, the propeller is arranged in the respective duct and is connected to the airframe, and the driving device is connected to the propeller(s) and is arranged on the airframe.

公开(公告)号：US09963226B2

公开(公告)日：2018-05-08

申请号：US15054485

申请日：2016-02-26

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GMBH

Inventor： Christian Wehle ,  Justus Steger ,  Marc Nothen ,  Stefan Probst ,  Antonia Horstmann

IPC: B64C27/82 ,  B64C27/20 ,  B64F5/10

CPC classification number: B64C27/82 ,  B64C27/20 ,  B64C2027/8272 ,  B64F5/10

Abstract: A tail assembly for a rotorcraft. The tail assembly is manufactured to include at least one transition structure provided in the tail assembly. The transition structure is longitudinally arranged between a longitudinal median boom portion and a tail fin. A power transmission shaft of the rotorcraft extends at least partly externally above a longitudinal median boom portion of the tail assembly. The transition structure includes at an entering region a cut-out elevation step, where is made a passing through opening for the power transmission shaft.

公开(公告)号：US09944389B2

公开(公告)日：2018-04-17

申请号：US15476612

申请日：2017-03-31

Applicant: Piasecki Aircraft Corporation

Inventor： John W. Piasecki ,  Frederick W. Piasecki ,  Brian Geiger ,  Douglas Johnson ,  David Pitcairn

IPC: B64C37/00 ,  B64C29/00 ,  B60F5/02 ,  B64C11/00 ,  B64C27/08 ,  B64C27/20 ,  B64C27/22 ,  B64C27/57 ,  B64D17/80 ,  B64C39/02 ,  B64C3/56 ,  G05D1/10

CPC classification number: B64C37/00 ,  B60F5/02 ,  B64C3/385 ,  B64C3/56 ,  B64C11/001 ,  B64C25/58 ,  B64C27/08 ,  B64C27/20 ,  B64C27/22 ,  B64C27/32 ,  B64C27/52 ,  B64C27/57 ,  B64C29/00 ,  B64C29/0033 ,  B64C39/00 ,  B64C39/02 ,  B64D17/80 ,  B64D25/00 ,  B64D2201/00 ,  G05D1/102

Abstract: An air module may be attached to a ground module. The air module may be equipped with a center of gravity effector to change the relative locations and hence the center of gravity of the air and ground modules when the modules are attached. The center of gravity effector may be active or passive or a combination of active and passive. The center of gravity effector may be combined with a center of lift effector to change the relative locations of the center of gravity and center of lift.

公开(公告)号：US20180099742A1

公开(公告)日：2018-04-12

申请号：US15837614

申请日：2017-12-11

Applicant: Coriolis Games Corporation

Inventor： Jacob Apkarian

IPC: B64C29/00 ,  B64F5/10 ,  B64C39/02

CPC classification number: B64C29/0033 ,  B64C27/20 ,  B64C27/52 ,  B64C39/024 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2211/00 ,  B64F5/10

Abstract: An aerial vehicle is includes a wing, first and second rotors, and a movement sensor. The first and second multicopter rotors are rotatably coupled to the wing, the first multicopter rotor is rotatable relative to the wing about a first lateral axis, and the second multicopter rotor is rotatable relative to the wing about a second lateral axis. Each multicopter rotor is coupled to each other multicopter rotor, wherein the multicopter rotors are restricted to collective synchronous rotation relative to the wing between a multicopter configuration and a fixed-wing configuration. The movement sensor is coupled to the multicopter rotors, wherein the movement sensor is positioned to rotate relative to the wing when the multicopter rotors rotate relative to the wing between the multicopter and fixed-wing configurations.

公开(公告)号：US20170291700A1

公开(公告)日：2017-10-12

申请号：US15477774

申请日：2017-04-03

Applicant: Mohyi Labs, LLC

Inventor： John Mohyi

IPC: B64C27/20 ,  B64C27/32 ,  B64C29/00

CPC classification number: B64C27/20 ,  B63H1/04 ,  B63H11/08 ,  B63H2011/082 ,  B64C11/001 ,  B64C27/32 ,  B64C29/0025 ,  B64C39/001 ,  B64C39/064 ,  B64C2201/027 ,  B64C2201/108

Abstract: A vehicle includes a propulsion system using one or more impellers as opposed to propellers. The impellers impart circumferential and radial velocity components to the working fluid, which may be air or water. The air is deflected by counter-vortex chambers in a shroud to convert the circumferential and radial velocity to an axial velocity aligned with the axis of rotation of the impeller.