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公开(公告)号：US20160136879A1
公开(公告)日：2016-05-19
申请号：US14546184
申请日：2014-11-18
Applicant: The Boeing Company
Inventor： Marc Rollo Matsen , Robert James Miller , Donald K. Dabelstein , Lee Charles Firth , Flint Matthew Jamison , Patrice K. Ackerman
CPC classification number: B29C65/3676 , B29C65/3632 , B29C65/3668 , B29C65/4815 , B29C65/5057 , B29C66/112 , B29C66/131 , B29C66/343 , B29C66/3494 , B29C66/524 , B29C66/532 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/73115 , B29C66/73921 , B29C66/8432 , B29C66/91421 , B29C66/91933 , B29L2031/3076 , H05B6/105 , B29K2307/04 , B29K2071/00 , B29K2063/00
Abstract: A susceptor welding tape for use in thermoplastic welding. The susceptor welding tape comprising a thermoplastic film and a plurality of non-continuous susceptor conductors imbedded within the thermoplastic film. The plurality of non-continuous susceptor conductors allow a resulting thermoplastic weld formed by the susceptor weld tape to be tuned to a desired engineering characteristic. For example, the plurality of conductors allow the resulting thermoplastic weld formed by the susceptor weld tape to be tuned to a desired conductivity, a desired residual stress and/or a desired moisture barrier of the resulting thermoplastic weld.
Abstract translation: 用于热塑性焊接的基座焊接带。 包含热塑性薄膜和嵌入在热塑性薄膜内的多个非连续感受体导体的基座焊带。 多个不连续的感受体导体允许由基座焊接带形成的所得到的热塑性焊接被调谐到期望的工程特性。 例如，多个导体允许由感受器焊接带形成的所得到的热塑性焊接被调谐到所需的导电性，所需的残余应力和/或所得的热塑性焊接的所需的湿气屏障。
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公开(公告)号：US09731812B2
公开(公告)日：2017-08-15
申请号：US14605421
申请日：2015-01-26
Applicant: The Boeing Company
Inventor： Steven Paul Walker , Flint Matthew Jamison , Kelly T. Jones
Abstract: An airfoil, a flap mechanism and an associated method are provided to controllably actuate a flap positioned proximate the trailing edge of an airfoil body. The flap mechanism includes a carrier beam hingedly connected to an airfoil body and also pivotally connected to a flap proximate the trailing edge of the airfoil body. The flap mechanism further includes an actuator, a first plurality of links and a second plurality of links. The first plurality of links is operably connected to the airfoil body, the actuator and the carrier beam. The first plurality of links causes the carrier beam to be rotated with respect to the airfoil body in response to actuation by the actuator. The second plurality of links is responsive to rotation of the carrier beam with respect to the airfoil body. The second plurality of links causes the flap to be rotated with respect to the carrier beam.
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公开(公告)号：US20160214705A1
公开(公告)日：2016-07-28
申请号：US14605421
申请日：2015-01-26
Applicant: The Boeing Company
Inventor： Steven Paul Walker , Flint Matthew Jamison , Kelly T. Jones
Abstract: An airfoil, a flap mechanism and an associated method are provided to controllably actuate a flap positioned proximate the trailing edge of an airfoil body. The flap mechanism includes a carrier beam hingedly connected to an airfoil body and also pivotally connected to a flap proximate the trailing edge of the airfoil body. The flap mechanism further includes an actuator, a first plurality of links and a second plurality of links. The first plurality of links is operably connected to the airfoil body, the actuator and the carrier beam. The first plurality of links causes the carrier beam to be rotated with respect to the airfoil body in response to actuation by the actuator. The second plurality of links is responsive to rotation of the carrier beam with respect to the airfoil body. The second plurality of links causes the flap to be rotated with respect to the carrier beam.
Abstract translation: 提供翼型件，翼片机构和相关联的方法以可控制地致动靠近翼型件主体的后缘定位的挡板。 翼片机构包括铰接地连接到翼型件主体并且还枢转地连接到靠近翼型件主体的后缘的翼片的托架梁。 翼片机构还包括致动器，第一多个连杆和第二多个连杆。 第一组多个连杆可操作地连接到翼型本体，致动器和承载梁。 响应于致动器的致动，第一多个连杆使得载体梁相对于翼型件本体旋转。 所述第二多个连杆响应所述载体梁相对于所述翼型件主体的旋转。 第二组多个连杆使翼片相对于承载梁旋转。
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