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公开(公告)号：US20230331370A1
公开(公告)日：2023-10-19
申请号：US17659671
申请日：2022-04-19
Applicant: The Boeing Company
Inventor： Jeffery Lee Marcoe , Marc R. Matsen , Waeil M. Ashmawi , Sahrudine Apdalhaliem
CPC classification number: B64C3/26 , B29C70/685 , B29C35/0805 , B29C2035/0811 , B29K2101/12
Abstract: Stiffened skin panels comprise alternating truss core portions and solid laminate portions sandwiched between inner and outer facesheets, all formed from a fiber reinforced thermoplastic. The components of the panels are co-consolidated using induction heating. The panels are stiffened with spars fastened to the solid laminate portions.
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2.发明申请公开(公告)号：US20200088661A1
公开(公告)日：2020-03-19
申请号：US16691896
申请日：2019-11-22
Applicant: The Boeing Company
Abstract: A computer-implemented method of determining moisture content of a composite structure is provided. The method includes performing a thermal analysis calculation on the composite structure to determine a temporal surface temperature profile of the composite structure based on temporal environmental parameter profiles, wherein the surface temperature profile is determined independently of a moisture content of the composite structure. The method also includes performing a moisture content analysis calculation on the composite structure to determine a moisture content of the composite structure, wherein the moisture content analysis calculation is based on the determined temporal surface temperature profile and a thickness of the composite structure. The thermal analysis calculation is performed iteratively with a first time period and the moisture content analysis calculation is performed iteratively with a second time period that is longer than the first time period.
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公开(公告)号：US10000299B2
公开(公告)日：2018-06-19
申请号：US14838442
申请日：2015-08-28
Applicant: THE BOEING COMPANY
Inventor： Waeil M. Ashmawi , Sahrudine Apdalhaliem
IPC: B64F5/00 , B29C65/02 , B01J35/06 , B64C1/10 , B01J31/06 , B29C65/54 , B29C65/48 , B29K701/12 , B29L9/00 , B29L31/30
CPC classification number: B64F5/40 , B01J31/06 , B29C65/14 , B29C66/112 , B29C66/116 , B29C66/532 , B29C73/22 , B29K2701/12 , B29K2713/00 , B29L2009/00 , B29L2031/3082 , B64C1/062 , B64C1/10 , B64C1/12
Abstract: Methods and apparatuses are disclosed relating to multilayer 3D textile composite materials containing self-healing resins for use as protective structures on stationary objects, and moving objects including, without limitation, vehicles including spacecraft and aircraft.
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公开(公告)号：US09919505B2
公开(公告)日：2018-03-20
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 , B29C70/54 , B32B37/00 , B32B37/10 , B32B37/18 , B29C33/38 , B29C33/48 , B29C70/44 , B29L31/30
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.
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5.发明申请公开(公告)号：US20170190137A1
公开(公告)日：2017-07-06
申请号：US15465029
申请日：2017-03-21
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
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.
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Patent Agency Ranking
6.发明申请METHODS AND SYSTEMS FOR DETERMINING AN ALLOWABLE MOISTURE CONTENT IN A COMPOSITE STRUCTURE 审中-公开用于确定复合结构中允许水分含量的方法和系统公开(公告)号：US20160370309A1
公开(公告)日：2016-12-22
申请号：US14745813
申请日：2015-06-22
Applicant: THE BOEING COMPANY
IPC: G01N25/00
CPC classification number: G01N25/00 , B64F5/60 , G01N17/00 , G01N33/442
Abstract: A method of determining an allowable moisture content of a composite structure includes performing a thermal analysis on the composite structure to determine a surface temperature profile of the composite structure. The surface temperature profile is determined independently of a moisture content of the composite structure. The method also includes performing a moisture analysis on the composite structure to determine an allowable moisture content of the composite structure such that the moisture analysis is based on the determined surface temperature profile.
Abstract translation: 确定复合结构的允许水分含量的方法包括对复合结构进行热分析以确定复合结构的表面温度分布。 独立于复合结构的水分含量来确定表面温度分布。 该方法还包括对复合结构进行水分分析以确定复合结构的允许含水量，使得水分分析基于确定的表面温度分布。
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7.发明申请ASSEMBLIES INCLUDING SHAPE MEMORY ALLOY FITTINGS AND COMPOSITE STRUCTURAL MEMBERS 有权包括形状记忆合金配件和复合结构件的组装公开(公告)号：US20160003280A1
公开(公告)日：2016-01-07
申请号：US14323529
申请日：2014-07-03
Applicant: The Boeing Company
Inventor： Waeil M. Ashmawi , Jaime C. Garcia , Sahrudine Apdalhaliem , Jeffery L. Marcoe , Moushumi Shome
IPC: F16B17/00
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.
Abstract translation: 提供了具有与形状记忆合金结构互锁的复合结构的组件和制造这种组件的方法。 联锁可以包括将形状记忆合金结构的互锁突起插入到复合结构的互锁开口中，并且加热形状记忆合金结构的至少该突起以激活合金并改变突起的形状。 这种形状变化与开口中的突起接合，使得突起不能从开口移除。 在使用热循环和变形的组合形成组件以实现特定的预激活和后激活形状之后，形状记忆合金结构可以被特别地训练。 预激活形状允许将互锁突起插入开口中，而后激活形状与开口内的互锁突起接合。 因此，形状记忆合金的激活将两个结构互锁。
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公开(公告)号：US11897602B2
公开(公告)日：2024-02-13
申请号：US17689169
申请日：2022-03-08
Applicant: The Boeing Company
Inventor： Muhammad Mustajab Malik , Waeil M. Ashmawi
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.
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公开(公告)号：US11685503B2
公开(公告)日：2023-06-27
申请号：US16866193
申请日：2020-05-04
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour , Waeil M. Ashmawi
CPC classification number: B64C1/064 , B29C53/02 , B29C65/48 , B29C66/729 , B29C70/30 , B29C70/545 , B29L2031/3076 , B64C2001/0072
Abstract: Described herein are stringer assemblies, such as blade stringers, and methods of forming thereof. A stringer assembly comprises a first fabric composite stiffener, a second fabric composite stiffener, and an intermediate tape composite stiffener, disposed between and connected to each of the first and second stiffeners. Using three separate components allows forming sharp bends, eliminating voids and gap fillers, and adding new features, such as edge reinforcements. Each of the first and second fabric composite stiffeners comprises a web portion, a flange portion, and a curved portion, positioned between the web and flange portions. The web portions surround and are attached to the intermediate tape composite stiffener and, in some examples, include tapered-out edges for additional rigidity. The flange portions are attached to the composite base. The curved portions conform to the flared-out edges of the intermediate tape composite stiffener, which extends and connects to the composite base.
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公开(公告)号：US20220033061A1
公开(公告)日：2022-02-03
申请号：US17376140
申请日：2021-07-14
Applicant: The Boeing Company
Inventor： Forouzan Behzadpour , Waeil M. Ashmawi , Sahrudine Apdalhaliem
Abstract: A movable surface of an aircraft has a front spar extending along a spanwise direction between opposing movable surface ends. The movable surface also includes a plurality of ribs defining a plurality of bays between adjacent pairs of the ribs. Each rib extends between the front spar and a trailing edge portion of the movable surface. The movable surface further includes an upper and a lower skin panels coupled to the ribs and the front spar. In addition, the bull surface includes a plurality of bead stiffeners coupled to an inner surface of at least one of the upper skin panel and the lower skin panel. The bead stiffeners within the bays are spaced apart from each other and are oriented non-parallel to the front spar and have a bead stiffener cap having opposing cap ends respectively locate proximate the front spar and the trailing edge portion.
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