-
公开(公告)号：US09981421B2
公开(公告)日：2018-05-29
申请号：US14332412
申请日：2014-07-16
Applicant: The Boeing Company
Inventor： Jeffery L. Marcoe , Sahrudine Apdalhaliem , Moushumi Shome
IPC: H01B17/20 , H01B17/38 , H01B7/08 , B29C61/06 , B64C3/48 , B64C3/52 , B29C70/30 , B32B15/08 , F03G7/06 , H05K1/05 , H05K1/16 , B29C70/88 , B29B11/16 , B64C3/44 , B64C27/72 , B64C3/54 , B29K71/00 , B29K267/00 , B29L31/30 , B29C53/82
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.
-
公开(公告)号：US09808996B2
公开(公告)日：2017-11-07
申请号：US14469575
申请日：2014-08-26
Applicant: The Boeing Company
Inventor： Jeffery L. Marcoe
IPC: B29C70/30 , B32B1/08 , B64C3/00 , B64C3/18 , B32B5/02 , B32B15/08 , B32B27/12 , B32B37/02 , B32B38/00
CPC classification number: B29C70/30 , B32B1/08 , B32B5/02 , B32B15/08 , B32B27/12 , B32B37/02 , B32B38/004 , B32B2262/10 , B32B2307/202 , B32B2307/544 , B32B2307/558 , B32B2311/18 , B32B2311/24 , B32B2311/30 , B32B2313/04 , B32B2605/00 , B32B2605/18 , B64C3/00 , B64C3/18 , Y02T50/43 , Y10T29/49826
Abstract: In an embodiment of the disclosure, there is provided a method of fabricating a thermoplastic torque box assembly. The method includes providing a plurality of braided thermoplastic tubular spar caps, connecting one or more connector elements to one or more of the braided thermoplastic tubular spar caps, and laying up an inner thermoplastic facesheet in a continuous manner around the one or more braided thermoplastic tubular spar caps. The method further includes attaching a plurality of skin panel stabilization elements to the inner thermoplastic facesheet to define four torque box side portions, laying up and attaching an outer thermoplastic facesheet in a continuous manner around the plurality of skin panel stabilization elements, and heating at an effective temperature and an effective pressure the thermoplastic torque box assembly.
-
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。
-
公开(公告)号：US20140209744A1
公开(公告)日：2014-07-31
申请号：US13751086
申请日：2013-01-26
Applicant: The Boeing Company
Inventor： Jeffery L. Marcoe , Paul S. Nordman , Stephen T. Brown , William G. Roeseler , Terry K. Isomura , Willard N. Westre
CPC classification number: B64C3/185 , B29C70/30 , B29D99/0014 , B32B3/12 , B32B5/022 , B32B5/024 , B32B5/12 , B32B5/18 , B32B2260/023 , B32B2260/046 , B32B2262/0261 , B32B2262/0269 , B32B2262/101 , B32B2262/106 , B32B2266/08 , B32B2307/54 , B32B2307/542 , B32B2307/718 , B32B2605/18 , B64C3/20 , Y02T50/43
Abstract: There is provided a box structure for carrying load having upper and lower composite integrated sandwich panels. The panels have facesheets sandwiching one or more core portions and adjacent dense packs oriented in an axial direction. The box structure further has a plurality of spars. Each spar has a web and web attachments and has a spar length in the axial direction. The plurality of spars are connected to the panels with the web attachments located at the dense packs. The facesheets are configured to carry primarily torsion and pressure loads in shear and no significant axial loads. The dense packs are configured to carry all significant box bending in axial tension and compression loads.
Abstract translation: 提供了一种用于承载具有上部和下部复合一体夹芯板的箱结构。 这些面板具有夹着一个或多个芯部分和沿轴向方向定向的相邻致密包装的面板。 盒结构还具有多个翼梁。 每个翼梁具有腹板和腹板附件，并且在轴向具有翼梁长度。 多个翼梁连接到面板，网片附件位于密集的包装上。 这些面板被配置为主要承受剪切中的扭转和压力载荷，并且没有显着的轴向载荷。 致密包装被配置为承受所有重要的箱体在轴向张力和压缩载荷下弯曲。
-
-
-
Search Results
24
records
(took 0.018 seconds)
