-
公开(公告)号：US11167840B2
公开(公告)日：2021-11-09
申请号：US16385542
申请日：2019-04-16
Applicant: The Boeing Company
Inventor： Samuel Lewis Block , Orion Parker Watson , Daniel Harvey Fletcher , Michael Robert Rush , Elizabeth Rose Benson
Abstract: Aircraft main landing gear drag brace backup fitting assemblies and related methods are described herein. An example aircraft wing disclosed herein includes a rear spar having a rear side and a front side opposite the rear side, a side-of-body rib coupled to the rear spar, a rib post disposed on the front side of the rear spar, where the rib post is to couple a second rib to the rear spar, a side-of-body fitting coupled to the side-of-body rib, an intercostal member coupled between the side-of-body fitting and the rib post, and a drag brace fitting disposed on the rear side of the rear spar. The drag brace fitting is coupled to the rib post and the side-of-body fitting via a first plurality of fasteners extending through the rear spar.
-
Patent Agency Ranking
公开(公告)号：US20210291958A1
公开(公告)日：2021-09-23
申请号：US16822545
申请日：2020-03-18
Applicant: The Boeing Company
Inventor： Tony Koung , Daniel Harvey Fletcher , Michael Robert Rush , Jacob Richard Medlang
Abstract: A monolithic joint system for a fuselage to wing joint in an aircraft is provided. The joint system comprises a first vertical flange, a base plate, a second vertical flange, and damage containment features associated with at least one of these components. The first vertical flange is configured to connect to a fuselage section of the aircraft and the second vertical flange is configured to connect to a rib web of a wing, while the base plate attaches outboard wing to inboard wing box. The first vertical flange, the base plate, and the second vertical flange are formed from a continuous piece of material. The damage containment features are configured to slow propagation of an active crack tip in the joint system during operation of the aircraft. Thus, the illustrative embodiments provide a one-piece joint system for the fuselage to wing joint of an aircraft.
-
公开(公告)号：US11358703B2
公开(公告)日：2022-06-14
申请号：US16822545
申请日：2020-03-18
Applicant: The Boeing Company
Inventor： Tony Koung , Daniel Harvey Fletcher , Michael Robert Rush , Jacob Richard Medlang
Abstract: A monolithic joint system for a fuselage to wing joint in an aircraft is provided. The joint system comprises a first vertical flange, a base plate, a second vertical flange, and damage containment features associated with at least one of these components. The first vertical flange is configured to connect to a fuselage section of the aircraft and the second vertical flange is configured to connect to a rib web of a wing, while the base plate attaches outboard wing to inboard wing box. The first vertical flange, the base plate, and the second vertical flange are formed from a continuous piece of material. The damage containment features are configured to slow propagation of an active crack tip in the joint system during operation of the aircraft. Thus, the illustrative embodiments provide a one-piece joint system for the fuselage to wing joint of an aircraft.
-
公开(公告)号：US20200331595A1
公开(公告)日：2020-10-22
申请号：US16385542
申请日：2019-04-16
Applicant: The Boeing Company
Inventor： Samuel Lewis Block , Orion Parker Watson , Daniel Harvey Fletcher , Michael Robert Rush , Elizabeth Rose Benson
Abstract: Aircraft main landing gear drag brace backup fitting assemblies and related methods are described herein. An example aircraft wing disclosed herein includes a rear spar having a rear side and a front side opposite the rear side, a side-of-body rib coupled to the rear spar, a rib post disposed on the front side of the rear spar, where the rib post is to couple a second rib to the rear spar, a side-of-body fitting coupled to the side-of-body rib, an intercostal member coupled between the side-of-body fitting and the rib post, and a drag brace fitting disposed on the rear side of the rear spar. The drag brace fitting is coupled to the rib post and the side-of-body fitting via a first plurality of fasteners extending through the rear spar.
-
公开(公告)号：US10029780B2
公开(公告)日：2018-07-24
申请号：US14902850
申请日：2013-08-09
Applicant: The Boeing Company
Inventor： Joshua Amory Ross , Shane Frank Cuda , Mark Ronald McLaughlin , Michael Robert Rush , Colin Lee Farr , David Bruce Smith , Nihar Ashokkumar Desai , Thomas Joseph Kennedy , Lyle Ray Deobald
IPC: B64C3/26 , B29D99/00 , B29C70/30 , B64C3/18 , B29K105/08
Abstract: A stiffened panel comprises a composite panel, and a stiffener including a base flange on the composite panel. The base flange is tapered towards the panel. The stiffened panel further comprises a composite overwrap layer on only the composite panel and a tapered surface of the base flange.
-
公开(公告)号：US20160176500A1
公开(公告)日：2016-06-23
申请号：US14902850
申请日：2013-08-09
Applicant: THE BOEING COMPANY
Inventor： Joshua Amory Ross , Shane Frank Cuda , Mark Ronald McLaughlin , Michael Robert Rush , Colin Lee Farr , David Bruce Smith , Nihar Ashokkumar Desai , Thomas Joseph Kennedy , Lyle Ray Deobald
CPC classification number: B64C3/26 , B29C70/30 , B29D99/0014 , B29K2105/0872 , B64C3/18 , Y02T50/43
Abstract: A stiffened panel comprises a composite panel, and a stiffener including a base flange on the composite panel. The base flange is tapered towards the panel. The stiffened panel further comprises a composite overwrap layer on only the composite panel and a tapered surface of the base flange.
Abstract translation: 加强板包括复合板，以及在复合板上包括基部凸缘的加强件。 底座法兰朝向面板逐渐变细。 加强板还包括仅在复合板上的复合外包层和基底凸缘的锥形表面。
-
-
-
-
-
Search Results
6
records
(took 0.014 seconds)
