公开(公告)号：US20190248467A1

公开(公告)日：2019-08-15

申请号：US16261486

申请日：2019-01-29

申请人： DASSAULT AVIATION

发明人： Aurélien MERLET ,  Zdenek JOHAN ,  Ximun LOYATHO ,  Gilbert ROGE

IPC分类号： B64C3/14 ,  B64C3/32

CPC分类号： B64C3/14 ,  B64C1/26 ,  B64C3/32 ,  B64C7/00 ,  B64C2003/149

摘要： An aircraft portion includes a fuselage oriented in a longitudinal direction, an airfoil made up of at least one pair of wings arranged on either side of the fuselage in a transverse direction orthogonal to the longitudinal direction, and an airfoil-fuselage junction fairing at the interface between the airfoil and the fuselage. The junction fairing has, in a vertical plane, a lower profile and, in a horizontal plane, a horizontal profile at the junction of the outer surface of the junction fairing with the convex side of each wing. The horizontal profile and/or the lower profile successively has, in the longitudinal direction, a convex front segment, a concave intermediate segment, and a convex rear segment.

公开(公告)号：US20190241245A1

公开(公告)日：2019-08-08

申请号：US16263877

申请日：2019-01-31

申请人： AIRBUS HELICOPTERS DEUTSCHLAND GMBH

发明人： Andreas RACK ,  Thomas JOACHIM ,  Rupert PFALLER

IPC分类号： B64C1/06

CPC分类号： B64C1/069 ,  B32B3/06 ,  B64C1/061 ,  B64C1/12 ,  B64C1/26 ,  B64C3/26 ,  B64C27/82 ,  F16B5/0088 ,  F16B11/006

摘要： A shear connection for interchangeably connecting two airframe parts of an aircraft. The shear connection may include first and second interface parts. The second interface part may overlap in the longitudinal direction at an overlap section with at least one of the first interface part and the first airframe part. The shear connection may further comprise means that rigidly and non-interchangeably attach the first interface part to the first airframe part and the second interface part to the second airframe part and a shear bolt that rigidly and interchangeably connects the second interface part with the at least one of the first interface part and the first airframe part at the overlap section, thereby interchangeably connecting the first and second airframe parts.

公开(公告)号：US20190185134A1

公开(公告)日：2019-06-20

申请号：US15846612

申请日：2017-12-19

申请人： Thomas Hsueh

发明人： Thomas Hsueh

IPC分类号： B64C1/26 ,  B64C3/38

CPC分类号： B64C1/26 ,  B64C1/064 ,  B64C3/38

摘要： The adjustable fuselage location method is based on the combined use of slots under fuselage longerons, saddles between fuselage and wing, straps, brackets, thread poles and nuts. Saddles installed under the fuselage provide an interface between the fuselage and wing. Straps wrap around the brackets inside fuselage longerons, saddles and wing box for fastening the wing to the fuselage. Thread poles are affixed on the brackets for guiding the traveling of fuselage in longitudinal direction. By turning the nuts on the poles, fuselage can be relocated on the wing. These adjusting mechanisms can be hided inside the longerons of fuselage and manipulated from inside of the fuselage.

公开(公告)号：US20180312248A1

公开(公告)日：2018-11-01

申请号：US16027848

申请日：2018-07-05

申请人： Skykar Inc.

发明人： Markus Leng

IPC分类号： B64C27/26 ,  B64D33/08 ,  B64D31/12 ,  B64D27/24 ,  B64D17/00 ,  B64C29/00 ,  B64C29/02 ,  B60L11/18 ,  B64C15/02 ,  B64C11/46 ,  B64C1/26 ,  B64C39/02

CPC分类号： B64C27/26 ,  B60L11/1805 ,  B60L11/1859 ,  B60L11/1861 ,  B64C1/26 ,  B64C11/46 ,  B64C15/02 ,  B64C29/00 ,  B64C29/0025 ,  B64C29/02 ,  B64C39/026 ,  B64D17/00 ,  B64D27/24 ,  B64D31/12 ,  B64D33/08

摘要： 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.

公开(公告)号：US20180155006A1

公开(公告)日：2018-06-07

申请号：US15801669

申请日：2017-11-02

申请人： AIRBUS OPERATIONS, S.L.

发明人： Alberto ARANA HIDALGO ,  Esteban MARTINO GONZÁLEZ ,  Jesús Javier VÁZQUEZ CASTRO ,  Pablo CEBOLLA GARROFE

IPC分类号： B64C5/02 ,  B64C1/26 ,  B64C3/28

CPC分类号： B64C5/02 ,  B64C1/065 ,  B64C1/26 ,  B64C3/28

摘要： An aircraft stabilizer (15, 17) with an enlarged area of laminar flow. The lateral skins (45a, 45b; 65a, 65b) of its torsion box (43; 63) include joggled areas (53a, 53b; 73a, 73b) as attachment areas of its leading edge (41; 61) which are arranged in a rearward position with respect to the forward most spar of the stabilizer (15, 17).

公开(公告)号：US20180086458A1

公开(公告)日：2018-03-29

申请号：US15712526

申请日：2017-09-22

申请人： Unmanned Innovation Inc. (dba Airware)

发明人： Thomas Skyler Sartorius ,  Calder Richmond Hughes ,  Julian Rene Alvarez ,  Sean David-Andrew Belardo

IPC分类号： B64C39/02 ,  B64D9/00 ,  B64C3/18

CPC分类号： B64C39/024 ,  B64C1/26 ,  B64C3/187 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/06 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2211/00 ,  B64D9/00

摘要： Disclosed here are unmanned aerial vehicle embodiments including some embodiments having a fuselage, tail, and wings including example embodiments with an adaptable payload section, alternatively or additionally, modular flight surfaces including tail, wings and motor, alternatively or additionally the vehicle configured for short landings with reversible thrust, alternatively or additionally, the unmanned aerial vehicle configured with direct connection to moveable flight control surfaces.

公开(公告)号：US20180050787A1

公开(公告)日：2018-02-22

申请号：US15238250

申请日：2016-08-16

申请人： The Boeing Company

发明人： Max U. Kismarton ,  Clayton L. Munk

IPC分类号： B64C3/18 ,  B64F5/00 ,  B64C3/26

CPC分类号： B64C3/182 ,  B29C70/00 ,  B29D99/0014 ,  B29L2031/3085 ,  B64C1/26 ,  B64C3/26 ,  B64F5/10

摘要： Systems and methods are provided for integrating structural components of a wing box. One embodiment is a system that includes outboard planked stringers within an outboard section of a wing box and are co-cured with composite skin at the outboard section. Each outboard planked stringer of the outboard section includes planar layers of Carbon Fiber Reinforced Polymer (CFRP) that are parallel with the composite skin at the outboard section, have fiber orientations aligned to bear tension and compression applied to the wing box, and each extend a different distance along the composite skin at the outboard section. The system also includes center planked stringers within the center section and are co-cured with composite skin at the center section. Each center planked stringer of the center section includes planar layers of CFRP that are parallel with the composite skin at the center section, have fiber orientations aligned to bear tension and compression applied to the wing box, and each extend a different distance along the skin at the center section.

公开(公告)号：US09884674B2

公开(公告)日：2018-02-06

申请号：US14440995

申请日：2013-10-17

申请人： United Technologies Corporation

发明人： Gabriel L. Suciu ,  Jesse M. Chandler

IPC分类号： B64C9/00 ,  B64C5/02 ,  B64D27/14 ,  B64C5/06 ,  B64C9/02 ,  B64C19/00 ,  B64D33/04 ,  F02K1/56 ,  F02K1/78 ,  B64C1/26

CPC分类号： B64C5/02 ,  B64C1/26 ,  B64C5/06 ,  B64C9/02 ,  B64C19/00 ,  B64D27/14 ,  B64D33/04 ,  F02K1/56 ,  F02K1/78

摘要： An aircraft includes a tail extending from a fuselage. The tail defines a structural box having first and second vertical stabilizers that support a horizontal stabilizer. The tail includes at least one sacrificial control surface and at least one primary control surface. The primary control surfaces maintain aircraft controllability in the event that the sacrificial control surface becomes inoperable.

公开(公告)号：US09856011B2

公开(公告)日：2018-01-02

申请号：US14819792

申请日：2015-08-06

申请人： The Boeing Company

发明人： Richard P. Topf ,  Jonathan D. Embler ,  Thomas R. Pinney

IPC分类号： B64C1/06 ,  B64C1/38 ,  B64C1/26 ,  B64C9/02 ,  B64C30/00

CPC分类号： B64C1/38 ,  B64C1/26 ,  B64C9/02 ,  B64C30/00 ,  Y02T50/44

摘要： Methods of joining a first aerostructure part with a second aerostructure part are disclosed, for example, methods of joining an airplane wing or control surface to an airplane fuselage or joining fins to a rocket body. The method comprises aligning a plurality of connection elements in a linear array within the second aerostructure part, wherein the connection elements comprise a plurality of flexible connection elements and at least one rigid connection element, and attaching the first aerostructure part to the second aerostructure part at a plurality of connection points with the plurality of connection elements. The second aerostructure part expands linearly at a greater rate when exposed to heat than the first aerostructure part resulting in a difference in linear distance between the first aerostructure part and the second aerostructure part and the flexible connection elements are configured to flex to accommodate for this linear distance difference.

公开(公告)号：US09849966B2

公开(公告)日：2017-12-26

申请号：US14975115

申请日：2015-12-18

申请人： The Boeing Company

发明人： Gregory M. Schmidt ,  Samuel Thomas Walton

IPC分类号： B64C1/26 ,  B64C39/12 ,  B64C3/18

CPC分类号： B64C1/26 ,  B64C3/185 ,  B64C5/02 ,  B64C5/04 ,  B64C39/12 ,  B64C2211/00

摘要： An aircraft includes a fuselage with structural interfaces for connection to any one or more of a variety of vertical tails, horizontal tails and canards. Vertical tails, horizontal tails and/or canards of different sizes, shapes, sweep angles, box chords, and/or root chords may connect to the fuselage without changing the structural layout or configuration of the fuselage structural interfaces.