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19 条记录 (耗时 0.012 秒)

    FLUID SYSTEMS THAT INCLUDE A CO-FLOW JET
    5.
    发明公开
    FLUID SYSTEMS THAT INCLUDE A CO-FLOW JET 审中-公开

    公开(公告)号：EP3476720A1

    公开(公告)日：2019-05-01

    申请号：EP18202156.8

    申请日：2018-10-23

    申请人： Coflow Jet, LLC

    发明人： ZHA, Gecheng

    IPC分类号： B64C3/10 ,  B64C3/36 ,  B64C21/02

    摘要： Fluid systems are described herein. An example embodiment of a fluid system has a first body portion (12), a second body portion (14), a plurality of supports, a plurality of fluid pressurizers (18), and a plurality of ducts (132). The first body portion and the second body portion cooperatively define an injection opening (58), a suction opening (104), and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.

    LEADING EDGE SYSTEMS AND METHODS FOR AEROSPACE VEHICLES
    8.
    发明公开
    LEADING EDGE SYSTEMS AND METHODS FOR AEROSPACE VEHICLES 审中-公开
    领先的飞行器系统和方法

    公开(公告)号：EP3272647A1

    公开(公告)日：2018-01-24

    申请号：EP17181831.3

    申请日：2017-07-18

    申请人： The Boeing Company

    发明人： STANLEY, Daniel C ,  KRUSE, John S ,  EMBLER, Jonathan D ,  O'HARA, Jeremy N

    IPC分类号： B64C3/18 ,  B64C3/36 ,  B64C39/02 ,  B64G1/58 ,  B64C1/38

    CPC分类号： B64C3/36 ,  B64C1/38 ,  B64C3/182 ,  B64C3/185 ,  B64C3/187 ,  B64C39/024 ,  B64G1/58

    摘要： There is provided a leading edge system (10) for an aerospace vehicle. The leading edge system has at least one structural member. The leading edge system further has a plurality of removable modules removably attached to the at least one structural member. Each removable module has a hollow box substructure (42) and at least one flange portion disposed along a first end (52) of the hollow box substructure. The leading edge system further has a plurality of first attachment elements (70) configured for attaching the at least one flange portion (54) of the removable module to a first end portion of the at least one structural member. The leading edge system further has a plurality of second attachment elements (74) configured for attaching a second end of the hollow box substructure opposite the flange portion, to a second end portion of the at least one structural member opposite the first end portion.

    摘要翻译： 提供了用于航空飞行器的前缘系统（10）。 前缘系统至少有一个结构构件。 前缘系统还具有可拆卸地连接到至少一个结构构件的多个可移除模块。 每个可移除模块具有中空盒子结构（42）和至少一个沿中空盒子下部结构的第一端（52）设置的凸缘部分。 前缘系统还具有多个第一附接元件（70），其被配置用于将可移除模块的至少一个凸缘部分（54）附接到至少一个结构构件的第一端部。 所述前缘系统还具有多个第二附接元件（74），所述第二附接元件被构造成用于将所述中空盒子底座的与所述凸缘部分相对的第二端附接到与所述第一端部相对的所述至少一个结构构件的第二端部。

    SOLID-LIQUID COMPOSITE STRUCTURES
    9.
    发明公开
    SOLID-LIQUID COMPOSITE STRUCTURES 审中-公开
    固体 - 液体复合结构

    公开(公告)号：EP3221214A1

    公开(公告)日：2017-09-27

    申请号：EP15861932.0

    申请日：2015-11-19

    申请人： Technion Research & Development Foundation Ltd.

    发明人： GAT, Amir ,  ELBAZ, Shai ,  MATIA, Yoav

    IPC分类号： B64C3/36 ,  B64C13/36 ,  B64C9/06 ,  F01D5/16 ,  B25J18/06

    CPC分类号： B64C3/185 ,  B29L2031/3085 ,  B64C1/34 ,  B64C3/38

    摘要： A pressurized, fluid-filled channel network embedded in an elastic structure, asymmetrically to the neutral plane, is used to create a deformation field within the structure by the pressurization of the embedded fluidic network, which can be applied in accordance with external forces acting on the structure. The deformation of the structure resulting from the liquid pressure and geometry of the network is related to a continuous deformation-field function. This enables the design of networks creating steady arbitrary deformation fields as well as to eliminate deformation created by external time varying forces, thus increasing the effective rigidity of the beam. By including the effects of the deformation created by the channel network on the beam inertia, the response of the beam to oscillating forces can be modified, enabling the design of channel networks which create pre-defined oscillating deformation patterns in response to external oscillating forces.

    摘要翻译： 嵌入在与中性面不对称的弹性结构中的加压的流体填充通道网络被用于通过嵌入式流体网络的加压在结构内产生变形场，其可以根据作用于 结构。 由液体压力和网络几何结构引起的结构变形与连续变形场函数有关。 这使得网络的设计能够产生稳定的任意形变场，并消除由外部时变力产生的变形，从而增加梁的有效刚度。 通过包括由通道网络产生的变形对束惯性的影响，可以修改束对振荡力的响应，从而能够设计响应于外部振荡力而产生预定义的振荡变形图案的通道网络。

    High heat transfer rate reusable thermal protection system
    10.
    发明公开
    High heat transfer rate reusable thermal protection system 审中-公开
    高传热率可重复使用的热保护系统

    公开(公告)号：EP2738104A3

    公开(公告)日：2017-05-24

    申请号：EP13193545.4

    申请日：2013-11-19

    申请人： The Boeing Company

    发明人： Herzberg, James S. ,  Budica, Robert J. ,  Chandler, Frank O. ,  Haney, Joseph W.

    IPC分类号： B64G1/58 ,  B64C1/38 ,  B23P15/26 ,  B64C3/36 ,  B64D13/00 ,  F28F13/06

    摘要： A system (100) and methods for high heat transfer rate reusable thermal protection are presented. A porous skin (110) comprises an exposed exterior surface (154) and a non-exposed surface (156), and a coolant reservoir (146) comprises perforations (118) coupled to the non-exposed surface, and valves (112). The valves regulate a flow of coolant (138) from the coolant reservoir to the porous skin in response to a temperature of the porous skin.

    摘要翻译： 提出了一种用于高传热率可重复使用的热保护的系统（100）和方法。 多孔蒙皮（110）包括暴露的外表面（154）和非暴露表面（156），冷却剂储存器（146）包括耦合到非暴露表面的穿孔（118）以及阀（112）。 响应于多孔蒙皮的温度，这些阀调节从冷却剂储存器到多孔蒙皮的冷却剂（138）的流动。