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

IPC: B64C1/26 ,  B64C1/06

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：US11286327B2

公开(公告)日：2022-03-29

申请号：US16704704

申请日：2019-12-05

Applicant: The Boeing Company

Inventor： Zak Eckel ,  Phuong Bui ,  Mark O'Masta ,  Jacob Hundley ,  Tony Koung

IPC: C08G8/10 ,  C08K5/07 ,  C08K5/5397 ,  C08K5/00 ,  C08K5/14 ,  C08G73/06 ,  C08K5/46 ,  B33Y10/00 ,  B33Y70/00 ,  B33Y80/00

Abstract: A fire retardant (FR) composite composition, including a liquid polymer, wherein the liquid polymer includes a photopolymer including at least two of a first molecule, a second molecule, and a third molecule, a FR thermoset, and a photoinitiator.

公开(公告)号：US11104096B2

公开(公告)日：2021-08-31

申请号：US16117676

申请日：2018-08-30

Applicant: THE BOEING COMPANY

Inventor： Jacob Michael Hundley ,  Mark R. O'Masta ,  Zak Charles Eckel ,  Alvin Escobar ,  Kenneth Cante ,  Tony Koung

IPC: B32B3/12 ,  B32B27/06

Abstract: A sandwich structure configured to be secured with a mechanical fastener includes a core assembly, which includes a polymer component configured for supporting a mechanical fastener connector insert. The core assembly further includes an open cellular component formed from a plurality of self-propagating photopolymer waveguides positioned around the polymer component, wherein a first portion of the plurality of self-propagating photopolymer waveguides is secured to and extends from the polymer component. Further included is a first face sheet secured to a first side of the core assembly, wherein the first portion of the plurality of self-propagating photopolymer waveguides has a distal end spaced apart from the polymer component and secured to the second face sheet.

公开(公告)号：US20200070465A1

公开(公告)日：2020-03-05

申请号：US16117676

申请日：2018-08-30

Applicant: THE BOEING COMPANY

Inventor： Jacob Michael Hundley ,  Mark R. O'Masta ,  Zak Charles Eckel ,  Alvin Escobar ,  Kenneth Cante ,  Tony Koung

IPC: B32B3/12 ,  B32B27/06

Abstract: A sandwich structure configured to be secured with a mechanical fastener includes a core assembly, which includes a polymer component configured for supporting a mechanical fastener connector insert. The core assembly further includes an open cellular component formed from a plurality of self-propagating photopolymer waveguides positioned around the polymer component, wherein a first portion of the plurality of self-propagating photopolymer waveguides is secured to and extends from the polymer component. Further included is a first face sheet secured to a first side of the core assembly, wherein the first portion of the plurality of self-propagating photopolymer waveguides has a distal end spaced apart from the polymer component and secured to the second face sheet.

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

IPC: B64C1/26 ,  B64C1/06

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：US09541177B2

公开(公告)日：2017-01-10

申请号：US14051957

申请日：2013-10-11

Applicant: The Boeing Company

Inventor： Thomas Martig ,  Frederick T. Calkins ,  Tony Koung

IPC: B64C13/00 ,  F16H25/14 ,  F03G7/00

CPC classification number: F16H25/14 ,  F03G7/00 ,  F03G7/065 ,  Y10T74/18888

Abstract: Ratcheting shape memory alloy actuators and systems and methods including the same are disclosed herein. The ratcheting shape memory alloy actuators include a ratcheting assembly that is operatively coupled to a first bracket and a shape memory alloy element that is operatively coupled to the ratcheting assembly and to a second bracket. The first bracket is configured to be operatively coupled to a first structure, while the second bracket is configured to be operatively coupled to a second structure. The shape memory alloy element is configured to apply a motive force to the ratcheting assembly upon deformation between a first conformation and a second conformation. The ratcheting assembly is configured to utilize the motive force to selectively adjust an orientation of the first structure relative to the second structure.

Abstract translation: 棘轮形状记忆合金致动器及其系统和方法在此公开。 棘轮状记忆合金致动器包括可操作地联接到第一支架的棘轮组件和可操作地联接到棘轮组件和第二支架的形状记忆合金元件。 第一支架构造成可操作地联接到第一结构，而第二支架被配置成可操作地联接到第二结构。 形状记忆合金元件构造成在第一构象和第二构象之间的变形时向棘轮组件施加动力。 棘轮组件构造成利用动力来选择性地调节第一结构相对于第二结构的取向。

公开(公告)号：US20150101452A1

公开(公告)日：2015-04-16

申请号：US14051957

申请日：2013-10-11

Applicant: The Boeing Company

Inventor： Thomas MARTIG ,  Frederick T. Calkins ,  Tony Koung

IPC: F16H25/14

CPC classification number: F16H25/14 ,  F03G7/00 ,  F03G7/065 ,  Y10T74/18888

Abstract: Ratcheting shape memory alloy actuators and systems and methods including the same are disclosed herein. The ratcheting shape memory alloy actuators include a ratcheting assembly that is operatively coupled to a first bracket and a shape memory alloy element that is operatively coupled to the ratcheting assembly and to a second bracket. The first bracket is configured to be operatively coupled to a first structure, while the second bracket is configured to be operatively coupled to a second structure. The shape memory alloy element is configured to apply a motive force to the ratcheting assembly upon deformation between a first conformation and a second conformation. The ratcheting assembly is configured to utilize the motive force to selectively adjust an orientation of the first structure relative to the second structure.

Abstract translation: 棘轮形状记忆合金致动器及其系统和方法在此公开。 棘轮状记忆合金致动器包括可操作地联接到第一支架的棘轮组件和可操作地联接到棘轮组件和第二支架的形状记忆合金元件。 第一支架构造成可操作地联接到第一结构，而第二支架被配置为可操作地联接到第二结构。 形状记忆合金元件构造成在第一构象和第二构象之间的变形时向棘轮组件施加动力。 棘轮组件构造成利用动力来选择性地调节第一结构相对于第二结构的取向。