公开(公告)号：US11247776B2

公开(公告)日：2022-02-15

申请号：US16372337

申请日：2019-04-01

申请人： The Boeing Company

发明人： Norman H. Princen ,  Robert H. Liebeck ,  Edward L. Lawson ,  Benjamin A. Harber

IPC分类号： B64C39/10 ,  B64D27/14 ,  B64D33/04 ,  B64D33/02

摘要： An aircraft having a blended-wing-body configuration includes a centerbody, a pair of wings, at least one pair of engines, a pair of air inlets, and a pair of exhaust outlets. The centerbody has an airfoil-shaped cross section, an aircraft centerline, an aft portion, an upper mold line, a lower mold line, and a pair of centerbody leading edge portions respectively on opposite sides of the aircraft centerline. The wings are integral with the centerbody. The pair of engines are located on opposite sides of the aircraft centerline and are mounted within the centerbody between the upper mold line and the lower mold line. The pair of air inlets are located respectively along the centerbody leading edge portions and are respectively fluidly coupled to the pair of engines. The pair of exhaust outlets our located in the aft portion of the centerbody and our respectively fluidly coupled to the pair of engines.

公开(公告)号：US20220033067A1

公开(公告)日：2022-02-03

申请号：US17501492

申请日：2021-10-14

申请人： Blended Wing Aircraft, Inc.

发明人： Mark Allan Page

IPC分类号： B64C21/02 ,  B64C39/10 ,  B64D29/04 ,  B64D33/02 ,  B64D33/04

摘要： Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.

公开(公告)号：US11208197B2

公开(公告)日：2021-12-28

申请号：US16042235

申请日：2018-07-23

申请人： Heka Aero LLC

发明人： Christopher Marot ,  Ricardo Romeu ,  Eric Holland

IPC分类号： B64C11/06 ,  F16M11/18 ,  F16M11/12 ,  B64C29/00 ,  B64C11/32 ,  B64C39/10 ,  B64C11/00 ,  B64C39/02

摘要： A fan for providing thrust including at least one blade, a hub adapted to carry the at least one blade, a hub motor adapted to rotate the hub 360 degrees about a first axis extending perpendicular to the at least one blade, a first mount adapted to carry the hub, and a first mount motor adapted to rotate the hub 360 degrees about a second axis perpendicular to the first axis and extending through the first mount first and second side securing points. The first mount may include a first mount first side securing point adapted to pivotally carry the hub, and a first mount second side securing point adapted to pivotally carry the hub.

公开(公告)号：US20210188438A1

公开(公告)日：2021-06-24

申请号：US17176208

申请日：2021-02-16

申请人： BOMBARDIER INC.

发明人： Siddhartho BANERJEE ,  Alexandre GALIN ,  Ian CHITTICK

IPC分类号： B64C39/10 ,  B64C1/00 ,  B64C3/14

摘要： A blended wing body aircraft wherein at least each profile section corresponding to the normalized half-span values from 0 to 0.2 has a thickness ratio having a nominal value within the range set forth in Table 1. Also, a blended wing body aircraft wherein at least each profile section corresponding to the normalized half-span values from 0.15 to 0.3 has a normalized chord having a nominal value within the range set forth in Table 1, and wherein a ratio between a maximum thickness of the center body and the chord length along the centerline has a nominal value of at least 16%. Also, a blended wing body aircraft wherein a region of the aircraft defined by normalized half-span values from 0.1 to 0.2 has a normalized chord having a dimensionless rate of change from −3.5 to −5.1, and a thickness ratio having a rate of change from −0.27 to −0.72.

公开(公告)号：US11034442B2

公开(公告)日：2021-06-15

申请号：US15755187

申请日：2016-08-30

申请人： UNIVERSITY OF MARYLAND, COLLEGE PARK

发明人： Evandro Gurgel Do Amaral Valente ,  Norman M. Wereley ,  Eduardo Gurgel Do Amaral Valente

IPC分类号： B64C37/00 ,  B64C15/12 ,  B64C29/00 ,  B64C39/02 ,  B64C39/10 ,  B64C17/02 ,  B64C5/02 ,  B64C11/46 ,  B64C19/00 ,  B64C29/02 ,  B64D29/00

摘要： The universal vehicle system is designed with a lifting body which is composed of a plurality of interconnected modules which are configured to form an aerodynamically viable contour of the lifting body which including a front central module, a rear module, and thrust vectoring modules displaceably connected to the front central module and operatively coupled to respective propulsive mechanisms. The thrust vectoring modules are controlled for dynamical displacement relative to the lifting body (in tilting and/or translating fashion) to direct and actuate the propulsive mechanism(s) as needed for safe and stable operation in various modes of operation and transitioning therebetween in air, water and terrain environments.

公开(公告)号：US10661882B2

公开(公告)日：2020-05-26

申请号：US15692524

申请日：2017-08-31

申请人： HORIZON HOBBY, LLC

发明人： James Haley ,  Mike McConville ,  Aaron Shell ,  Chris Huhn ,  Dustin Buescher

IPC分类号： B64C1/26 ,  A63H27/00 ,  B64C39/02 ,  B64C39/10

摘要： A radio-controlled (RC) aircraft has a wing lock and disconnect mechanism. The RC aircraft has a structural member and a wing that disconnects from a fuselage. The RC aircraft has a lock mechanism, a wing structural member recess, a fuselage structural member recess, a lock recess, and an aperture. The lock mechanism couples to the wing and is adapted to fit within the lock recess of the fuselage. The wing structural member receives the structural member. The fuselage structural members recess corresponds to the wing structural member recess. The lock recess receives the lock mechanism. The wing disconnects from the fuselage by unlocking the lock mechanism. The structural member fits within the wing structural member recess and the fuselage structural member recess.

公开(公告)号：US20190341592A1

公开(公告)日：2019-11-07

申请号：US16422327

申请日：2019-05-24

申请人： Airbus Operations GmbH

发明人： Peter Linde ,  Peter Rostek

IPC分类号： H01M2/10 ,  B64D27/24 ,  B64C39/10 ,  B64D41/00

摘要： An arrangement of a structural element for an aerospace vehicle and a battery set. The structural element extends along a longitudinal direction and has a main web, a first flange and a second flange. The flanges extend away from the main web and are defined by flange edges extending along the longitudinal direction. The first flange, the second flange and the main web form a U-shaped profile defining a cavity. The battery set includes a baseplate and at least one battery on the baseplate. The structural element and the battery set are formed such that the baseplate can be releasably attached to the structural element. The baseplate extends between flange edges and the battery is received in the cavity when the battery set is mounted to the structural element. Further, an aerospace vehicle including such an arrangement, a structural element for an aerospace vehicle and a battery set are disclosed.

公开(公告)号：US20190055006A1

公开(公告)日：2019-02-21

申请号：US16167968

申请日：2018-10-23

申请人： UNITED TECHNOLOGIES CORPORATION

发明人： Razvan Virgil Florea ,  William T. Cousins ,  Thomas G. Tillman ,  David J. Arend ,  John D. Wolter

IPC分类号： B64C21/04 ,  B64D33/02 ,  B64D27/20 ,  B64C39/10 ,  B64C1/16 ,  B64D29/04

摘要： A hybrid wing aircraft has an engine embedded into a body of the hybrid wing aircraft. The embedded engine has a fan that is received within a nacelle. The body of the aircraft provides a boundary layer over a circumferential portion of a fan. A system delivers additional air to correct fan stability issues raised by the boundary layer.

公开(公告)号：US20180079505A1

公开(公告)日：2018-03-22

申请号：US15268059

申请日：2016-09-16

申请人： Laszlo Molnar

发明人： Laszlo Molnar

IPC分类号： B64C39/10 ,  B64C13/50 ,  B64C9/00 ,  B64D31/00

CPC分类号： B64C39/10 ,  B64C1/06 ,  B64C3/10 ,  B64C3/16 ,  B64C9/00 ,  B64C13/503 ,  B64C25/00 ,  B64C2001/0045 ,  B64D11/06 ,  B64D27/20 ,  B64D31/00 ,  B64D37/04 ,  B64D47/08 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/46

摘要： An oval lifting-body airplane may generate lift without wings. It may be propelled by a pivoting propulsion engine attached to an upper surface, allowing it to fly substantially parallel to the oval's major axis or the oval's minor axis, allowing different configurations for landing and takeoff than for cruising.

公开(公告)号：US09849968B2

公开(公告)日：2017-12-26

申请号：US14560964

申请日：2014-12-04

申请人： Jonathon J. Linch ,  Kyle M. Rahrig

发明人： Jonathon J. Linch ,  Kyle M. Rahrig

IPC分类号： B64C11/00 ,  B64C11/08 ,  B64C11/18 ,  B64C39/02 ,  B64C39/10

CPC分类号： B64C11/001 ,  B64C11/08 ,  B64C11/18 ,  B64C39/024 ,  B64C39/10 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/162 ,  B64C2220/00 ,  Y02T50/12

摘要： A propeller includes a hub coaxially surrounding a longitudinal axis. A ring shroud coaxially surrounds the longitudinal axis and is spaced radially from the hub. At least one propeller blade is fixedly attached to both the hub and ring shroud and extends radially therebetween for mutual rotation therewith. At least one stub blade has a first stub end radially spaced from a second stub end. The first stub end is fixedly attached to a selected one of the hub and ring shroud. The second stub end is cantilevered from the first stub end and is radially interposed between the first stub end and the selected one of the hub and ring shroud.