公开(公告)号：US1783529A

公开(公告)日：1930-12-02

申请号：US31224228

申请日：1928-10-13

申请人： WATERMAN WALDO D

发明人： WATERMAN WALDO D

IPC分类号： B64C3/38

CPC分类号： B64C3/385 ,  B64C1/26

公开(公告)号：US1290004A

公开(公告)日：1918-12-31

申请号：US16858817

申请日：1917-05-14

申请人： CURTISS AEROPLANE & MOTOR CO

发明人： ZIMMERMANN PAUL G

CPC分类号： B64C1/26

公开(公告)号：US1246027A

公开(公告)日：1917-11-06

申请号：US15660217

申请日：1917-03-22

申请人： CURTISS AEROPLANE & MOTOR CO

发明人： KLECKLER HENRY

CPC分类号： B64C1/26

公开(公告)号：US12084184B2

公开(公告)日：2024-09-10

申请号：US18050850

申请日：2022-10-28

申请人： SE AERONAUTICS INC

发明人： William Tyler Mathews ,  Harold Irven Mathews, Jr.

IPC分类号： B64C39/08 ,  B64C1/00 ,  B64C1/26 ,  B64C9/24 ,  B64C23/06 ,  B64D27/20 ,  B64F5/10

CPC分类号： B64C39/08 ,  B64C1/26 ,  B64C9/24 ,  B64C23/069 ,  B64D27/20 ,  B64F5/10 ,  B64C2001/0072

摘要： Various aerospace vehicle systems and methods are disclosed. In one embodiment, a fuel efficient, low emissions aerospace vehicle includes a fuselage having a fineness ratio of equal to or greater than 8. The fuselage is comprised of at least 50% composite materials. The aerospace vehicle also includes a first wing, a second wing, and a third wing coupled to the fuselage, each wing having an aspect ratio of equal to or greater than 35. The wings each have a span within 10% of one another and an aspect ratio within 10% of one another. Each wing is comprised of at least 50% composite materials. The aerospace vehicle also includes at least one stabilizing unit coupled to the fuselage. The stabilizing unit includes first and second stabilizer surfaces configured in a V-tail configuration. The aerospace vehicle further includes at least one propulsion system.

公开(公告)号：US11780598B2

公开(公告)日：2023-10-10

申请号：US17694721

申请日：2022-03-15

申请人： HONDA MOTOR CO., LTD.

发明人： Yuji Ishitsuka

IPC分类号： B64D27/14 ,  B64C3/00 ,  B64C1/26 ,  B64C27/22 ,  B64C1/06 ,  B64D27/24

CPC分类号： B64D27/14 ,  B64C1/26 ,  B64C3/00 ,  B64C1/061 ,  B64C1/064 ,  B64C1/068 ,  B64C27/22 ,  B64D27/24

摘要： An aircraft includes a fuselage, a wing disposed above the fuselage, a pylon connecting the wing to the fuselage, and a plurality of internal combustion engines housed in the fuselage. The pylon vertically traverses the fuselage and is fixed to an upper portion and a lower portion of the fuselage. Among the plurality of internal combustion engines, a first internal combustion engine and a second internal combustion engine are disposed bilaterally symmetrically about the pylon and are fixed to the pylon.

公开(公告)号：US11745852B2

公开(公告)日：2023-09-05

申请号：US18071469

申请日：2022-11-29

申请人： EnExSys Research Inc.

发明人： James Henke

IPC分类号： B64C9/04 ,  B64C9/06 ,  B64C9/18 ,  B64C27/06 ,  B64C27/82 ,  B64C3/54 ,  B64C1/26 ,  B64C3/18

CPC分类号： B64C3/546 ,  B64C1/26 ,  B64C3/185 ,  B64C9/04 ,  B64C9/06 ,  B64C9/18 ,  B64C27/06 ,  B64C27/82 ,  B64C2027/8272

摘要： A simple, safe, and inexpensive flight control system in an aircraft. An anti-torque system for a rotary-wing aircraft has an airfoil with a first surface extending from a first trailing edge and a leading edge, and a second surface extending from a second trailing edge to join the first surface at the leading edge. The airfoil has a first moveable deflector panel pivotally coupled to the first trailing edge, and a second moveable deflector panel pivotally coupled to the second trailing edge. Means are provided to pivot the deflector panels in unison about their respective pivot axes to alter the direction of travel of the airflow downstream of the pivot axes over the surfaces of the deflector panels, thereby producing a lift in a direction perpendicular to the airflow to counteract the torque applied on the aircraft. The flight control system may be arranged within a fixed-wing aircraft.

公开(公告)号：US20230174216A1

公开(公告)日：2023-06-08

申请号：US18160658

申请日：2023-01-27

申请人： Amazon Technologies, Inc.

发明人： Jon T. Braam ,  Kyle Thomas Miller ,  Bradley David Urban ,  Raffaele Cipolletta ,  Rahul Bhardwaj ,  Dominic Shiosaki

IPC分类号： B64C1/06 ,  B64F5/10 ,  B64C1/10 ,  B64C1/26 ,  B64C29/02 ,  B64C39/06 ,  B64C39/02

CPC分类号： B64C1/061 ,  B64F5/10 ,  B64C1/10 ,  B64C1/26 ,  B64C29/02 ,  B64C39/062 ,  B64C39/024

摘要： An airframe design may include a bonded frame or assembly, and one or more components that may be removably attached to the bonded frame. The bonded frame may include struts, central bulkheads, a tail section, a plurality of wing sections, and motor mounts that are adhered together using adhesive. The one or more attachable components may include a forward fuselage, motors, propellers, motor pod fairings, stabilizer fins, and landing gear that are attached using fasteners. The bonded frame may reduce the number of parts of the airframe design and may also reduce complexity, cost, and weight, while also increasing stiffness and strength. Further, the various attachable components may facilitate fabrication, assembly, and maintenance of an aerial vehicle having the airframe design.

公开(公告)号：US11661170B2

公开(公告)日：2023-05-30

申请号：US16608545

申请日：2018-04-26

申请人： BOMBARDIER INC.

发明人： Michael Murphy ,  Jack Araujo ,  Gary Shum ,  George Bradley

IPC分类号： B64C1/26 ,  B64C3/18

CPC分类号： B64C1/26 ,  B64C3/182

摘要： Assemblies and methods for facilitating the assembly of aircraft wings to a fuselage are disclosed. In some embodiments, a wing unit includes features that are configured to define one of more parts of a pressure vessel that is partially defined by the fuselage portion. In some embodiments, the aircraft assemblies disclosed herein comprise one or more first structural interfaces that permit positional adjustment between the wing unit and the fuselage portion so that one or more second structural interfaces may be finished only after such positional adjustment. In some embodiments, the aircraft assemblies disclosed herein comprise one or more structural interfaces that are disposed outside of the wing unit in order to eliminate or reduce the need for assembly personnel to access the interior of the wing unit to carry out the structural assembly of the wing unit to the fuselage portion.

公开(公告)号：US20190210709A1

公开(公告)日：2019-07-11

申请号：US16074248

申请日：2017-01-31

申请人： TUDOR CROSSFELT, LLP

发明人： Samuel Hall BOUSFIELD

IPC分类号： B64C3/56 ,  B64C1/26 ,  B64C37/00 ,  B60F5/02

CPC分类号： B64C3/56 ,  B60F5/02 ,  B64C1/26 ,  B64C37/00

摘要： Some embodiments described herein relate to a wing that is coupled to a body of a vehicle and configured to rotate forward from a deployed configuration, in which the wing extends from the body to a retracted configuration in which a tip portion of the wing is closer to a nose portion of the body than a root portion of the wing is to the nose portion. A hinged beam having a first portion pivotably coupled to a second portion is configured to transmit loads associated with flight from the wing to the body.

公开(公告)号：US09957035B2

公开(公告)日：2018-05-01

申请号：US14172035

申请日：2014-02-04

申请人： Texas A&M University System

发明人： John Valasek ,  James Franklin May ,  Andrew Beckett ,  Cecil C. Rhodes, Jr.

IPC分类号： B64C1/26 ,  B64C1/22 ,  B64C39/02 ,  B64C39/04

CPC分类号： B64C1/26 ,  B64C1/22 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/128 ,  B64C2211/00

摘要： The present invention relates to an aircraft. The aircraft includes a fuselage module for receiving a payload. The fuselage module includes a plurality of internal connections. The aircraft includes a wing module adjustably coupled to the fuselage module and a tail module coupled to the wing module. The wing module may be adjusted relative to the fuselage module to adjust a location of an aerodynamic center of the aircraft to maintain a pre-determined distance between the location of the aerodynamic center of the aircraft and the location of the center of gravity of the aircraft. A main landing gear may be adjusted relative to the fuselage module to adjust the location of the aerodynamic center of the aircraft to maintain a pre-determined distance between the location of the aerodynamic center of the aircraft and the location of the center of gravity of the aircraft.