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公开(公告)号：US09457494B2
公开(公告)日：2016-10-04
申请号：US14481851
申请日：2014-09-09
Applicant: The Boeing Company
Inventor： Moushumi Shome , Janet Mary Layng , Waeil M. Ashmawi , Sahrudine Apdalhaliem
CPC classification number: B29C35/0805 , B29C35/02 , B29C70/44 , B29C2035/0855 , B29L2031/3055 , B29L2031/3067 , B29L2031/3076
Abstract: Method and apparatus for curing a composite laminate. The apparatus comprising an electromagnetic radiation source creating electromagnetic microwave energy in an enclosed volume and a heating source for providing a convective airflow in the enclosed volume. A composite laminate assembly comprising a composite laminate is placed in the enclosed volume, wherein the composite laminate of the composite laminate assembly is cured by both the electromagnetic microwave energy created by the electromagnetic radiation source, and the convective airflow provided by the heating source. A vacuum bag may be placed over the composite laminate assembly. A source may be activated such that a vacuum within the vacuum bag is created according to design specifications.
Abstract translation: 固化复合层压板的方法和装置。 该装置包括在封闭容积中产生电磁微波能量的电磁辐射源和用于在封闭容积中提供对流气流的加热源。 包括复合层压材料的复合层压组件放置在封闭的体积中，其中复合层压组件的复合叠层体由电磁辐射源产生的电磁微波能量和由加热源提供的对流气流两者固化。 真空袋可以放置在复合层压组件上。 源可以被激活，使得根据设计规范创建真空袋内的真空。
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公开(公告)号：US20160067888A1
公开(公告)日：2016-03-10
申请号：US14481851
申请日：2014-09-09
Applicant: The Boeing Company
Inventor： Moushumi Shome , Janet Mary Layng , Waeil M. Ashmawi , Sahrudine Apdalhaliem
CPC classification number: B29C35/0805 , B29C35/02 , B29C70/44 , B29C2035/0855 , B29L2031/3055 , B29L2031/3067 , B29L2031/3076
Abstract: Method and apparatus for curing a composite laminate. The apparatus comprising an electromagnetic radiation source creating electromagnetic microwave energy in an enclosed volume and a heating source for providing a convective airflow in the enclosed volume. A composite laminate assembly comprising a composite laminate is placed in the enclosed volume, wherein the composite laminate of the composite laminate assembly is cured by both the electromagnetic microwave energy created by the electromagnetic radiation source, and the convective airflow provided by the heating source. A vacuum bag may be placed over the composite laminate assembly. A source may be activated such that a vacuum within the vacuum bag is created according to design specifications.
Abstract translation: 固化复合层压板的方法和装置。 该装置包括在封闭容积中产生电磁微波能量的电磁辐射源和用于在封闭容积中提供对流气流的加热源。 包括复合层压材料的复合层压组件放置在封闭的体积中，其中复合层压组件的复合叠层体由电磁辐射源产生的电磁微波能量和由加热源提供的对流气流两者固化。 真空袋可以放置在复合层压组件上。 源可以被激活，使得根据设计规范创建真空袋内的真空。
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公开(公告)号：US20160016355A1
公开(公告)日：2016-01-21
申请号：US14332412
申请日：2014-07-16
Applicant: The Boeing Company
Inventor： Jeffery L. Marcoe , Sahrudine Apdalhaliem , Moushumi Shome
CPC classification number: B29C61/0625 , B29B11/16 , B29C53/822 , B29C70/30 , B29C70/88 , B29K2071/00 , B29K2267/00 , B29L2031/3085 , B32B15/08 , B32B2250/02 , B32B2605/18 , B64C3/48 , B64C3/52 , B64C2003/445 , B64C2003/543 , B64C2027/7288 , F03G7/065 , H05K1/056 , H05K1/165 , H05K2201/0129 , H05K2201/0308 , Y02T50/34 , Y02T50/43
Abstract: Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.
Abstract translation: 整合热塑性和形状记忆合金材料的系统和工艺，形成能够改变其形状的自适应复合结构。 例如，自适应复合结构可以被设计为用作多功能自适应翼飞行控制表面。 用于这种自适应复合结构的其它应用包括在可变区域的风扇喷嘴，小翼，整流罩，电梯，方向舵或具有优选可控的形状的空气动力学表面的其它飞行器部件。 材料系统可以通过用热塑性塑料和形状记忆合金材料的丝束进行重叠（交织）整合，或者可以将每种材料的单独层合并（例如，使用感应加热）来制造不需要分开的飞行控制表面 致动。
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34.发明申请METHODS AND SYSTEMS FOR DETERMINING OPTICAL PROPERTIES FOR LIGHT TRANSMITTED MEDIUMS 审中-公开用于确定光传输介质的光学性质的方法和系统公开(公告)号：US20150362402A1
公开(公告)日：2015-12-17
申请号：US14301686
申请日：2014-06-11
Applicant: THE BOEING COMPANY
Inventor： Sahrudine Apdalhaliem , Kimberly D. Meredith
CPC classification number: G01M11/0228 , G01B11/0625 , G01J3/28 , G01J3/42 , G01M11/005 , G01N21/55 , G01N21/59
Abstract: Methods and systems for determining optical properties for light transmitted mediums are provided. One method includes acquiring one or more measured values indicative of a reflectance for a material, acquiring one or more measured values indicative of a transmittance for the material, and determining a set of calculated values for an index of refraction coefficient and an extinction coefficient from the one or more measured values indicative of reflectance and transmittance, respectively. The method includes identifying a calculated value from the set of calculated values for the index of refraction coefficient and a calculated value from the set of calculated values for the extinction coefficient that are within a threshold determined by the difference between the one or more measured values indicative of the reflectance or transmittance and a predicted reflectance or transmittance, respectively. The method includes determining a reflectance and transmittance for the material using the calculated values.
Abstract translation: 提供了用于确定光透射介质光学特性的方法和系统。 一种方法包括获取指示材料的反射率的一个或多个测量值，获取表示材料的透射率的一个或多个测量值，以及确定来自所述材料的折射系数和消光系数的计算值的集合 分别表示反射率和透射率的一个或多个测量值。 该方法包括从针对折射系数的计算值的集合中识别计算值，以及从消光系数的计算值的集合中计算出的值在由一个或多个测量值之间的差确定的阈值内 的反射率或透射率以及预测的反射率或透射率。 该方法包括使用所计算的值确定材料的反射率和透射率。
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公开(公告)号：US11407486B2
公开(公告)日：2022-08-09
申请号：US16683848
申请日：2019-11-14
Applicant: THE BOEING COMPANY
Inventor： Waeil M. Ashmawi , Sahrudine Apdalhaliem , Jaime C. Garcia
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.
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Patent Agency Ranking
公开(公告)号：US10774858B2
公开(公告)日：2020-09-15
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
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.
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公开(公告)号：US20180243972A1
公开(公告)日：2018-08-30
申请号：US15963890
申请日：2018-04-26
Applicant: The Boeing Company
Inventor： Jeffery L. Marcoe , Sahrudine Apdalhaliem , Moushumi Shome
IPC: B29C61/06 , B64C3/48 , B29C70/30 , B29C70/88 , B64C3/52 , F03G7/06 , H05K1/16 , B32B15/08 , B29B11/16 , H05K1/05 , B29K267/00 , B29K71/00 , B29C53/82 , B29L31/30 , B64C3/44 , B64C3/54 , B64C27/72
CPC classification number: B29C61/0625 , B29B11/16 , B29C53/822 , B29C70/222 , B29C70/30 , B29C70/32 , B29C70/88 , B29K2071/00 , B29K2267/00 , B29L2031/3085 , B32B15/08 , B32B2250/02 , B32B2605/18 , B64C3/48 , B64C3/52 , B64C2003/445 , B64C2003/543 , B64C2027/7288 , F03G7/065 , H05K1/056 , H05K1/165 , H05K2201/0129 , H05K2201/0308 , Y02T50/34 , Y02T50/43
Abstract: Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.
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公开(公告)号：US09827697B2
公开(公告)日：2017-11-28
申请号：US14473184
申请日：2014-08-29
Applicant: The Boeing Company
Inventor： Allan Tien , Samson Souksamrane , Sahrudine Apdalhaliem
IPC: B29C43/52 , B29C35/02 , B29C43/56 , B29C70/88 , B29K105/08 , B29K307/04 , B29L9/00
CPC classification number: B29C43/52 , B29C35/02 , B29C35/0227 , B29C35/0266 , B29C35/0272 , B29C35/0288 , B29C43/56 , B29C70/882 , B29K2105/08 , B29K2307/04 , B29K2995/0013 , B29L2009/00
Abstract: Systems and methods for curing complex fiber-reinforced composite structures utilize two distinct heat sources. A first heat source is utilized for heating a complex fiber-reinforced composite structure from within an internal portion of the complex fiber-reinforced composite structure. A second heat source is utilized for heating the complex fiber-reinforced composite structure from an external surface of the complex fiber-reinforced composite structure.
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公开(公告)号：US09682766B2
公开(公告)日：2017-06-20
申请号：US14746127
申请日：2015-06-22
Applicant: The Boeing Company
Inventor： Sahrudine Apdalhaliem , Waeil M. Ashmawi
IPC: B64C1/14
CPC classification number: B64C1/1484 , B64C1/1492
Abstract: A thermal barrier apparatus for a window system includes a closed curve-shaped plate having a plurality of concentric channels, a plurality of walls each defining adjacent concentric channels, each of the walls including a plurality of openings between adjacent concentric channels, an outer wall formed on an outer peripheral edge of the closed curve-shaped plate, the outer wall including a plurality of openings, and an inner wall formed on an inner peripheral edge of the closed curve-shaped plate including a plurality of openings. The plurality of openings and concentric channels are configured to provide an air flow path for conduction of air through the thermal barrier apparatus to an exterior of the thermal barrier apparatus.
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40.发明授权公开(公告)号：US09664183B2
公开(公告)日：2017-05-30
申请号：US14593106
申请日：2015-01-09
Applicant: THE BOEING COMPANY
Inventor： Sahrudine Apdalhaliem , Moushumi Shome , Kimberly D. Meredith , Waeil M. Ashmawi , Morteza Safai , Frederick T. Calkins
Abstract: Aspects of the present disclosure generally relate to an SMA actuator that includes a cooling device disposed within a torque tube. In one aspect, the cooling device includes a sliding sleeve, an expandable sleeve, and plurality of cooling fins coupled to the expandable sleeve. Axial movement of the sliding sleeve relative to the expandable sleeve facilitates radial expansion of the expandable sleeve and urges the cooling fins into contact with the torque tube. The cooling fins function as heat sinks when in contact with the torque tube to facilitate the removal of heat from the torque tube to increase the cooling rate of the torque tube. During heating of the torque tube, the cooling fins may be spaced apart from the torque tube to reduce the thermal mass that is heated, thus increasing the heating rate of the torque tube.
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