公开(公告)号：US11518515B1

公开(公告)日：2022-12-06

申请号：US17367752

申请日：2021-07-06

申请人： Government of the United States, as represented by the Secretary of the Air Force

发明人： Nicholas Newsted ,  Joseph Allison ,  David Adler ,  Brandon Lance ,  Robert Dome ,  Arthur Chappelka ,  Wendell Thompson

IPC分类号： B64C27/00 ,  B64D1/08 ,  B64D1/14 ,  B64C27/54 ,  B64C27/20

摘要： An apparatus for air dropping equipment and supplies from an aircraft is disclosed herein. The apparatus includes a canister having a rotor system configured to slow the descent at a predetermined altitude to a desired landing speed via auto-rotation and/or with motor assist. The rotor system is configured to prevent the container from spinning about its longitudinal axis during the descent.

公开(公告)号：US11440650B2

公开(公告)日：2022-09-13

申请号：US15504525

申请日：2015-09-30

申请人： SIKORSKY AIRCRAFT CORPORATION

发明人： Erez Eller ,  Matthew A. White ,  David H. Hunter

IPC分类号： B64C27/10 ,  F16F15/02 ,  B64C27/00 ,  B64C27/14 ,  B64C1/00 ,  B64C7/00 ,  B64C13/18 ,  B64C13/50 ,  B64C19/00 ,  B64C27/12 ,  B64C27/32 ,  B64C27/33 ,  B64C27/473 ,  B64C27/48 ,  B64C27/51 ,  B64C27/52 ,  B64C27/54 ,  B64C27/78 ,  B64C27/80 ,  B64C27/82 ,  B64D39/00 ,  B64D39/06 ,  B64D45/02 ,  F16H37/02 ,  G05D1/00 ,  G05D1/02 ,  B64C27/16 ,  B64C13/04 ,  G05D1/08 ,  B64C27/57 ,  B64D35/06 ,  B64C27/467 ,  F02C9/28 ,  F16D13/52 ,  F16D13/72 ,  F16D13/74 ,  B64C27/08

摘要： An aircraft is provide including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. At least one flight control computer configured to independently control the upper rotor assembly and the lower rotor assembly through a fly-by-wire control system. A plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, wherein the sensors provide the sensor data to the flight control computer.

公开(公告)号：US20220194569A1

公开(公告)日：2022-06-23

申请号：US17503537

申请日：2021-10-18

申请人： The Boeing Company

发明人： Gary E. Georgeson ,  Joseph L. Hafenrichter

IPC分类号： B64C27/22 ,  B64C27/54 ,  B64C3/38 ,  B64C27/32 ,  B64D27/24 ,  B64C9/26 ,  B64C13/00 ,  G05D1/10

摘要： An aerial vehicle includes a wing body. The aerial vehicle includes a plurality of rotors coupled to the wing body. Each one of the rotors includes a plurality of rotor blades. The aerial vehicle includes a drive assembly configured to rotate the rotors. The aerial vehicle includes a controller configured to selectively control thrust produced by each one of the rotors. Selective control of the thrust produced by each one of the rotors induces a pitch motion of the aerial vehicle to transition the aerial vehicle between a horizontal flight state and a vertical flight state. In the horizontal flight state, the wing body is approximately horizontal and a collective thrust from the rotors is directed forward. In the vertical flight state, the wing body is approximately vertical and the collective thrust from the plurality rotors is directed upward.

公开(公告)号：US20210403149A1

公开(公告)日：2021-12-30

申请号：US16912513

申请日：2020-06-25

申请人： Bell Textron Inc.

发明人： Brad Joseph Passe ,  Nicholas Ralph Carlson ,  George Matthew Thompson

IPC分类号： B64C27/08 ,  B64C27/37 ,  B64C27/473 ,  B64C27/54 ,  B64C39/02 ,  B64C29/00

摘要： A rotor system includes a rotor assembly and a duct system. The rotor assembly includes rotor blades extending from a mast axis and configured to rotate about the mast axis. The duct assembly includes a moveable duct portion and a stationary duct portion. In a first duct configuration, the moveable duct portion surrounds a first portion of the rotor assembly, the stationary duct portion surrounds a second portion of the rotor assembly, and the moveable duct portion and the stationary duct portion enclose the rotor assembly. In a second duct configuration, the stationary duct portion surrounds the second portion of the rotor assembly, and the moveable duct portion is moved away from the first portion of the rotor assembly, such that the rotor assembly is not enclosed.

公开(公告)号：US20210253246A1

公开(公告)日：2021-08-19

申请号：US17252201

申请日：2019-06-17

申请人： ZEVA INC.

发明人： Stephen Tibbitts ,  Ben Gould

IPC分类号： B64C39/02 ,  B64C29/02 ,  B64C39/06 ,  B64C39/10 ,  B64D47/02 ,  B64C25/04 ,  B64C9/00 ,  B64C1/14 ,  B64D43/00 ,  B64D47/08 ,  B64D27/24 ,  B64C27/54 ,  B64C13/04 ,  B64D31/00 ,  B60L50/60 ,  B60L15/20

摘要： An electric vertical take-off and landing aircraft having a disc-shaped blended wing-body that houses power sources and controls. Thrust pod arms are attached to the blended wing-body and each arm has a one of a set of thruster pairs. An ingress/egress hatch is attached to the rear surface. Navigation and strobe lights are located on the outside edge. Front landing gear is attached to the upper surface including pair of parallel motor pod struts. Main landing gear is attached proximate the trailing edge and a set of right and left elevons is attached to the rear surface proximate the main landing gear. A cockpit area including a viewing window is formed on the blended-wing.

公开(公告)号：US10960974B2

公开(公告)日：2021-03-30

申请号：US16041512

申请日：2018-07-20

申请人： FLIR Unmanned Aerial Systems AS

发明人： Petter Muren ,  Trygve Frederik Marton ,  Ivar Johnsrud ,  Pal Hagh Sandberg ,  Christian Moengen ,  Jo Eyvin Bjaarstad

IPC分类号： B64C27/00 ,  B64C27/625 ,  B64C27/54 ,  B64C27/48 ,  A63H27/00 ,  G05D1/08 ,  B64C27/635 ,  B64C39/02

摘要： The present embodiments disclose a torque dependent and resonant operating thrust-generating rotor assembly including a cyclic pitch control system for controlling tilting moments about a longitudinal rotor blade axis of one or more rotor blades, in order to control the pitch angle of the rotor blades and thereby also the horizontal movements of a helicopter vehicle or a rotary wing aircraft. A rotor torque assembly of the rotor assembly is further configured to operate in resonance, thereby providing a resonant gain effecting a rotational offset in relation to changes in torque generated by the motor.

公开(公告)号：US20200377207A1

公开(公告)日：2020-12-03

申请号：US16338970

申请日：2016-10-03

申请人： AERONEXT INC.

发明人： Youichi SUZUKI

IPC分类号： B64C27/52 ,  B64C27/20 ,  B64D9/00 ,  B64C27/54 ,  B64C29/00

摘要： A delivery rotary-wing aircraft has a plurality of rotary wings, a central portion to which a plurality of arms for supporting the rotary wings are connected, a first mounting portion for loading a package, a second mounting portion which is located on the opposite side to the first mounting portion as viewed from the central portion, a first supporting member for coupling the first mounting portion with the central portion, and a connection portion between the central portion and the first supporting member. The center point of lift occurring in the rotary-wing aircraft with the rotation of the plurality of rotary wings and the center point of gravity of the rotary-wing aircraft coincide with the center point of the connection portion. The first supporting member is equipped with an adjustment mechanism for vertically downwardly extending the length of the first supporting member.

公开(公告)号：US10689104B2

公开(公告)日：2020-06-23

申请号：US15590736

申请日：2017-05-09

申请人： Textron Innovations Inc.

发明人： Glenn Alan Shimek ,  Nathan Patrick Green ,  Robert Alan Self ,  Mark Adam Wiinikka

IPC分类号： B64C27/51 ,  B64C27/82 ,  B64C27/54 ,  B64C27/48 ,  B64C27/473 ,  B64C27/39 ,  B29L31/08 ,  B64C27/32 ,  B64C27/00

摘要： A system and method for attaching a damper to a tail rotor blade includes a cuff that is integral with the rotor blade. The cuff has upper and lower lugs formed by extending a skin over a blade core of the rotor blade. The skin extends past the blade core to the root end of the rotor blade. The rod end of the damper is inserted into an opening between the lugs. The rod end of the damper is coupled to the blade with a bolt through aligned holes in the lugs. The cuff also couples the rotor blade to the grip inside the cuff. The cuff includes a same material as that forming the skin. Sacrificial buffer pads are applied to interior faces of the lugs. The buffer pads permit a distance between the lugs to be machined within a tolerance without removing skin from the cuff.

公开(公告)号：US20200023960A1

公开(公告)日：2020-01-23

申请号：US16285958

申请日：2019-02-26

申请人： AEROVIRONMENT, INC.

发明人： Dana J. Taylor ,  Phillip T. Tokumaru ,  Bart Dean Hibbs ,  William Martin Parks ,  David Wayne Ganzer ,  Joseph Frederick King

IPC分类号： B64C29/00 ,  B64C39/02 ,  G05D1/08 ,  B64C11/32 ,  B64C27/605 ,  B64C29/02 ,  B64C27/26 ,  B64C27/54 ,  B64D27/24

摘要： A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing.

公开(公告)号：US10353402B2

公开(公告)日：2019-07-16

申请号：US15501130

申请日：2015-06-22

申请人： SIKORSKY AIRCRAFT CORPORATION

发明人： Steven E. Spoldi

IPC分类号： G05D1/08 ,  B64C27/00 ,  B64C27/06 ,  B64C27/54

摘要： A method and system for vector limiting of a rotor control volume for a helicopter with one or more controllers configured to issue a displacement command during a flight maneuver and a computer operably connected to the one or more controllers and configured to receive signals with a processor indicative of a displacement command for a rotor during a flight maneuver; determine with the processor an origination point for a command vector in a reference frame; determine with the processor the command vector in the reference frame; determine with the processor a command radius for the command vector; compare with the processor the command radius with values of estimated command radii in a look-up table; and determine with the processor a control volume limited command in response to the comparing of the command radius with the estimated command radius.