公开(公告)号：US09470828B1

公开(公告)日：2016-10-18

申请号：US14744795

申请日：2015-06-19

Applicant: The Boeing Company

Inventor： Sahrudine Apdalhaliem ,  Waeil M. Ashmawi ,  Kimberly Dawn Meredith

IPC: G02F1/03 ,  G02B5/23 ,  G02B5/20 ,  G02F1/01 ,  B64C1/14

CPC classification number: G02B5/23 ,  B64C1/1484 ,  B64D2011/0061 ,  G02B5/208 ,  G02F1/0126 ,  G02F1/153 ,  G02F2202/14

Abstract: A window system and method of attenuating light in a window system for improving usefulness and reliability of an electronic dimmable window in the window system. An automatically adjusting photochromatic material is integrated into a window pane of the window system such that the electronic dimmable window is positioned between the automatically adjusting photochromatic material in the window pane and a dust cover of the window system. The automatically adjusting photochromatic material is formulated to attenuate incoming light in a local area of the photochromatic material in response to a solar flux intensity of the incoming light in the local area being greater than or equal to a threshold intensity while areas outside the local area of the photochromatic material that are subjected to solar flux intensity less than the threshold intensity do not attenuate incoming light.

Abstract translation: 一种在窗系统中衰减光的窗口系统和方法，用于提高窗系统中电子可调光窗的有用性和可靠性。 将自动调节的色素材料集成到窗系统的窗格中，使得电子可调光窗口位于窗玻璃中的自动调节的光色材料和窗系统的防尘罩之间。 配置自动调整的色素材料以响应于局部区域中的入射光的太阳能通量强度大于或等于阈值强度而衰减光色材料的局部区域中的入射光，而局部区域外的区域 经受太阳能通量强度小于阈值强度的光色材料不会衰减入射光。

公开(公告)号：US20160023406A1

公开(公告)日：2016-01-28

申请号：US14340914

申请日：2014-07-25

Applicant: THE BOEING COMPANY

Inventor： Moushumi Shome ,  Sahrudine Apdalhaliem ,  Frederick T. Calkins ,  Waeil M. Ashmawi ,  Kimberly Meredith

IPC: B29C70/34 ,  B32B37/10 ,  B32B37/18 ,  B29C70/54 ,  B32B37/00

CPC classification number: B32B37/1036 ,  B29C33/38 ,  B29C33/485 ,  B29C70/446 ,  B29C70/54 ,  B29K2905/00 ,  B29L2031/3076 ,  B32B37/0046 ,  B32B37/18 ,  B32B2605/18 ,  Y02T50/43

Abstract: In one or more aspects of the present disclosure, a mandrel is disclosed. The mandrel having a shape memory alloy (SMA) shell having a longitudinal axis, an interior extending along the longitudinal axis and an exterior contour, the SMA shell being configured to interface with a structure to be cured, and at least one SMA actuation member disposed within the interior and connected to the SMA shell, where the at least one SMA actuation member is configured to exert pressure against the SMA shell effecting an interface pressure between the exterior contour of the SMA shell and the structure to be cured where the exterior contour has a predetermined actuated shape that corresponds to a predetermined cured shape of the structure to be cured.

Abstract translation: 在本公开的一个或多个方面，公开了一种心轴。 心轴具有具有纵向轴线的形状记忆合金（SMA）壳体，沿着纵向轴线延伸的内部和外部轮廓，SMA壳体被配置为与要固化的结构相接触，并且至少一个SMA致动构件设置在 在内部并且连接到SMA壳体，其中至少一个SMA致动构件构造成对SMA壳施加压力，从而影响SMA外壳的外部轮廓与外部轮廓具有的待固化结构之间的界面压力 对应于要固化的结构的预定固化形状的预定的致动形状。

公开(公告)号：US20150321441A1

公开(公告)日：2015-11-12

申请号：US14465911

申请日：2014-08-22

Applicant: The Boeing Company

Inventor： Jeffery Lee Marcoe ,  Marc Rollo Matsen ,  Waeil M. Ashmawi ,  Jaime C. Garcia ,  Sahrudine Apdalhaliem ,  John B. Moser ,  Brett I. Lyons ,  Moushumi Shome ,  Kay Y. Blohowiak

IPC: B32B1/08 ,  B29C70/20 ,  B32B5/02 ,  B29C70/46

CPC classification number: B32B1/08 ,  B29C33/52 ,  B29C70/205 ,  B29C70/462 ,  B29C2035/0811 ,  B32B5/024 ,  B32B2262/106 ,  B32B2605/08 ,  B32B2605/12 ,  B32B2605/18 ,  D04C1/06

Abstract: Manufacturing a thermoplastic composite tubular structure embedded with a first load fitting comprising the steps of braiding a first plurality of inner layers of thermoplastic composite material around a soluble, expandable mandrel. A first load fitting is positioned on the first plurality of inner layers of thermoplastic composite material. A second plurality of outer layers of thermoplastic composite material is braided around the first load fitting and the mandrel so as to form an overbraided mandrel embedded with the first load fitting. The overbraided mandrel is installed into a matched tooling assembly and heated at a specified heating profile in order to consolidate the first plurality of inner layers of thermoplastic composite material and the second plurality of outer layers of thermoplastic composite material with the first load fitting so as to form a thermoplastic composite tubular structure embedded with the first load fitting. A second load fitting may be positioned on the first plurality of inner layers of thermoplastic composite material.

Abstract translation: 制造嵌入有第一负载配件的热塑性复合管状结构，其包括在可溶性可扩张心轴周围编织第一组多个热塑性复合材料内层的步骤。 第一负载配件位于热塑性复合材料的第一多个内层上。 围绕第一负载配件和心轴编织第二多个热塑性复合材料外层，以便形成嵌入第一负载配件的外包芯。 将所覆盖的心轴安装到匹配的模具组件中并以特定的加热轮廓加热，以便将第一多个热塑性复合材料的内层和第二多个热塑性复合材料的外层与第一负载配件固结，以便 形成嵌入第一负载配件的热塑性复合管状结构。 第二负载配件可以被定位在热塑性复合材料的第一多个内层上。

公开(公告)号：US20220402590A1

公开(公告)日：2022-12-22

申请号：US17805795

申请日：2022-06-07

Applicant: The Boeing Company

Inventor： Waeil M. Ashmawi ,  Zayd I. Abdel-Kamel ,  Sahrudine Apdalhaliem

IPC: B64C3/18 ,  B29C70/68

Abstract: Examples are disclosed herein that relate to vehicles, composite parts, and three-dimensional (3D) textile preforms for composite parts. In one example, a 3D textile preform for a composite part comprises a flange portion and a stiffener portion extending upwardly from the flange portion. The stiffener portion comprises a first wall portion that extends from the flange portion and a second wall portion that extends from the flange portion at a location spaced from the first wall portion. A connecting portion connects the first wall portion and the second wall portion at a location spaced from the flange portion.

公开(公告)号：US20220297824A1

公开(公告)日：2022-09-22

申请号：US17689169

申请日：2022-03-08

Applicant: The Boeing Company

Inventor： Muhammad Mustajab Malik ,  Waeil M. Ashmawi

IPC: B64C25/04 ,  B64C3/18

Abstract: A support structure to mount landing gear to a wing spar of an aircraft. The support structure includes a trunnion assembly having a first trunnion and a second trunnion that are connected together with the first trunnion positioned on a first side of the wing spar and a second trunnion positioned on an opposing second side of the wing spar. The trunnion assembly is configured to support a first section of the landing gear.

公开(公告)号：US20210147058A1

公开(公告)日：2021-05-20

申请号：US16683848

申请日：2019-11-14

Applicant: The Boeing Company

Inventor： Waeil M. Ashmawi ,  Sahrudine Apdalhaliem ,  Jaime C. Garcia

IPC: B64C1/14

Abstract: A window clamp system and method are to secure a window pane to a window frame of a vehicle. The window clamp system includes a mounting bracket configured to be secured to the window frame, one or more ratchets coupled to the mounting bracket, and a spring clip configured to move in relation to the mounting bracket and the one or more ratchets. The spring clip is configured to engage a seal positioned around the window pane.

公开(公告)号：US10744722B2

公开(公告)日：2020-08-18

申请号：US15797314

申请日：2017-10-30

Applicant: The Boeing Company

Inventor： Angelo Rossi ,  Jeffery L. Marcoe ,  Marc R. Matsen ,  Aaron W. Bartel ,  Waeil M. Ashmawi ,  Sahrudine Apdalhaliem ,  Adriana Willempje Blom-Schieber ,  David Reusch

IPC: B29C65/72 ,  B29C70/50 ,  B29C70/24 ,  B29C65/62 ,  D04C1/06 ,  B29C33/44 ,  B29D99/00 ,  B29B11/16

Abstract: A radius filler includes a plurality of fibers encapsulated in resin and braided into a braided radius filler. The braided radius filler has a substantially triangular shape with concave radius filler side surfaces and a substantially planar radius filler base surface.

公开(公告)号：US10063164B2

公开(公告)日：2018-08-28

申请号：US14987115

申请日：2016-01-04

Applicant: The Boeing Company

Inventor： Sahrudine Apdalhaliem ,  Waeil M. Ashmawi

IPC: H02N2/18 ,  B64D41/00 ,  B60R16/03 ,  B64C3/18 ,  H02J7/00 ,  F16B5/02

CPC classification number: H02N2/18 ,  B60R16/03 ,  B64C3/185 ,  B64C3/187 ,  B64D41/00 ,  F16B5/02 ,  H02J7/0052 ,  Y02T50/44 ,  Y02T50/53

Abstract: A system and method for harvesting energy from a vehicle, e.g., an aircraft, in operation. A plurality of piezoelectric members are coupled between structural members in the vehicle. A first portion of the plurality of piezoelectric members are non-resonant piezoelectric spacers coupled between structural members subject to a constant load during operation of the vehicle. A second portion of the plurality of piezoelectric members are resonant piezoelectric fillers coupled between structural members subject to a cyclical load during operation of the vehicle. Electrical conversion circuitry is coupled to each of the plurality of piezoelectric members for converting the output of each piezoelectric member to usable electrical energy. The electrical conversion circuitry is coupled to an energy storage device for storing the usable electrical energy and/or to an interface circuit for supplying energy for use in an electrical system in the vehicle.

公开(公告)号：US20180065314A1

公开(公告)日：2018-03-08

申请号：US15797314

申请日：2017-10-30

Applicant: The Boeing Company

Inventor： Angelo Rossi ,  Jeffery L. Marcoe ,  Marc R. Matsen ,  Aaron W. Bartel ,  Waeil M. Ashmawi ,  Sahrudine Apdalhaliem ,  Adriana Willempje Blom-Schieber ,  David Reusch

IPC: B29C65/72 ,  B29D99/00 ,  B29C33/44 ,  B29C65/62 ,  B29C70/24 ,  B29C70/50 ,  D04C1/06

Abstract: A radius filler includes a plurality of fibers encapsulated in resin and braided into a braided radius filler. The braided radius filler has a substantially triangular shape with concave radius filler side surfaces and a substantially planar radius filler base surface.

公开(公告)号：US20170292547A1

公开(公告)日：2017-10-12

申请号：US15630745

申请日：2017-06-22

Applicant: The Boeing Company

Inventor： Waeil M. Ashmawi ,  Jaime C. Garcia ,  Sahrudine Apdalhaliem ,  Jeffery L. Marcoe ,  Moushumi Shome

IPC: F16B1/00

CPC classification number: F16B1/0014

Abstract: Provided are assemblies having composite structures interlocked with shape memory alloy structures and methods of fabricating such assemblies. Interlocking may involve inserting an interlocking protrusion of a shape memory alloy structure into an interlocking opening of a composite structure and heating at least this protrusion of the shape memory alloy structure to activate the alloy and change the shape of the protrusion. This shape change engages the protrusion in the opening such that the protrusion cannot be removed from the opening. The shape memory alloy structure may be specifically trained prior to forming an assembly using a combination of thermal cycling and deformation to achieve specific pre-activation and post-activation shapes. The pre-activation shape allows inserting the interlocking protrusion into the opening, while the post-activation shape engages the interlocking protrusion within the opening. As such, activation of the shape memory alloy interlocks the two structures.