公开(公告)号：US11820483B2

公开(公告)日：2023-11-21

申请号：US17518844

申请日：2021-11-04

申请人： The Boeing Company

发明人： Daniel Cox ,  Danilo Vukosav ,  Evgeniy M. Potupchik ,  Francisco Del Valle ,  Ryan Matthew Slater ,  Timothy Robert Portway

IPC分类号： B64C1/06 ,  B64C1/26

CPC分类号： B64C1/065 ,  B64C1/064 ,  B64C1/069 ,  B64C1/26

摘要： Described herein are aircraft, comprising rear spar integration assemblies, and methods of manufacturing these aircraft. Specifically, an aircraft comprises a keel beam and a center wing box, comprising a rear spar. The rear spar is attached to the keel beam using a rear spar integration assembly. The assembly comprises a rear spar stiffener, attached to the rear spar, and having a stiffener load axis. The assembly also comprises and a keel beam fitting, attached to the keel beam, and having a fitting load axis. The rear spar stiffener is also attached to the keel beam fitting, e.g., using splice plates. More specifically, the fitting load axis is offset relative to the stiffener load axis along the primary axis of the aircraft. This offset is designed to compensate for a bending moment at the keel beam-rear spar interface, which allows reducing the size and/or the number of fasteners needed.

公开(公告)号：US11724801B2

公开(公告)日：2023-08-15

申请号：US16178892

申请日：2018-11-02

申请人： Textron Systems Corporation

发明人： Sean Marshall Baity ,  David D. Billingsley ,  Brad S. Galloway ,  Richard M. Chapman

IPC分类号： B64C29/00 ,  B64C39/10 ,  B64C1/26 ,  B64C11/44 ,  B64C11/46 ,  B64C39/02 ,  B64D27/24 ,  G05D1/08

CPC分类号： B64C29/0033 ,  B64C39/10 ,  B64C1/26 ,  B64C11/44 ,  B64C11/46 ,  B64C39/024 ,  B64C2039/105 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64C2211/00 ,  B64D27/24 ,  G05D1/0858

摘要： An aircraft includes an airframe having a fixed-wing section and a plurality of articulated electric rotors, at least some of which are variable-position rotors having different operating configurations based on rotor position. A first operating configuration is a vertical-flight configuration in which the rotors generate primarily vertical thrust for vertical flight, and a second operating configuration is a horizontal-flight configuration in which the rotors generate primarily horizontal thrust for horizontal fixed-wing flight. Control circuitry independently controls rotor thrust and rotor orientation of the variable-position rotors to provide thrust-vectoring maneuvering. The fixed-wing section may employ removable wing panels so the aircraft can be deployed both in fixed-wing and rotorcraft configurations for different missions.

公开(公告)号：US20230147045A1

公开(公告)日：2023-05-11

申请号：US17958722

申请日：2022-10-03

申请人： John Galaz

发明人： John Galaz

IPC分类号： B64B1/30 ,  B64C39/04 ,  B64D27/24 ,  B64D27/10 ,  B60L8/00 ,  B64C1/26 ,  B64B1/20 ,  B64B1/22 ,  B64D47/08 ,  B64B1/14 ,  F02B61/04 ,  H01M10/46

CPC分类号： B64B1/30 ,  B64C39/04 ,  B64D27/24 ,  B64D27/10 ,  B60L8/003 ,  B64C1/26 ,  B64B1/20 ,  B64B1/22 ,  B64D47/08 ,  B64B1/14 ,  F02B61/04 ,  H01M10/465 ,  B64D2211/00 ,  B64D2027/026

摘要： A solar powered airship includes a cabin, at least one fuselage having an interior volume filled with a volume of a lighter-than-air gas such as helium, and a wing affixed to the fuselage. A plurality of solar panels are affixed to the wing and to the fuselage. A plurality of rotors are affixed to the wing, wherein each rotor is powered via an electric motor having a battery that is operably connected to the plurality of solar panels, thereby allowing for continuous flight. The solar powered airship may further include propellors, which may also be powered via the solar panels, or which may include gasoline powered motors. The solar powered airship can include various configurations and numbers of fuselages, wings, rotors, and propellors.

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.