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    • 6. 发明授权
    • Inflatable air inlet duct
    • 充气进气管
    • US4121606A
    • 1978-10-24
    • US845172
    • 1977-10-25
    • Charles L. HollandGeorge B. Nicoloff
    • Charles L. HollandGeorge B. Nicoloff
    • B64D33/02
    • B64D33/02B64D2033/0286Y10T137/0536
    • An air inlet duct for a jet propulsion missile or other vehicle which is movable between a housed, pre-launch position and an extended or deployed flight position. A method of manufacturing the duct is also disclosed. The duct system includes a flexible leading edge attached to a double-wall inflatable duct body. Drop threads extend between the duct body walls to hold an exact desired contour when the duct is inflated. A pivotable plate moves the inflatable duct between a housed, deflated, position and an inflated flight position. Manufacture of the inflatable duct is basically accomplished by preparing a foamed plastic form in the desired duct wall shape, covering the form with fabric, stitching through the foam and fabric, coating the fabric with a flexible sealing compound, dissolving away the foamed plastic and attaching the resulting inflatable duct to other missile components.
    • 用于喷气推进导弹或其他车辆的进气管道,其可在容纳的预发射位置和延伸或部署的飞行位置之间移动。 还公开了制造管道的方法。 管道系统包括连接到双壁可充气管道主体的柔性前缘。 当管道膨胀时,落纱线在管体壁之间延伸以保持精确期望的轮廓。 可枢转板将可充气管道移动到容纳的,放气的位置和充气的飞行位置之间。 充气管道的制造基本上是通过制备所需导管壁形状的泡沫塑料形式,用织物覆盖形式,缝合通过泡沫和织物,用柔性密封化合物涂覆织物,将泡沫塑料和附着物 所产生的充气管道与其他导弹部件。
    • 8. 发明授权
    • Foil insert honeycomb sandwich brazing process and resulting structure
    • 箔插入式蜂窝夹心钎焊工艺及结构
    • US4477012A
    • 1984-10-16
    • US449149
    • 1982-12-13
    • Charles L. HollandDale L. Jennings
    • Charles L. HollandDale L. Jennings
    • B23K1/00B23K31/00
    • B23K1/0014
    • A method of brazing the nodes of honeycomb core material and the top and bottom panels to the honeycomb core material to form a sandwich structure. The method comprises the insertion in selected cells of the core, a coil or loop formed of normally flat resilient braze foil ribbon under tension and then releasing the tension to allow the braze foil, coil or loop to be urged against the cell walls under its own resiliency. The top and bottom panels are then installed over the core adjacent to the cell faying edges to form top and bottom surfaces. Pressure is then applied from the panels toward the honeycomb core material. The temperature of the sandwich structure is then elevated until the braze foil is caused to melt. Capillary attraction causes the now liquid braze material to flow into the interstices between the cell nodes and between the faying edges of the honeycomb core cells and the adjacent panels.
    • 将蜂窝芯材料的节点和顶板和底板钎焊到蜂窝芯材料上以形成夹层结构的方法。 该方法包括在芯的选定单元中插入一个线圈或环,该线圈或环由通常平坦的弹性钎焊箔片形成在张力下,然后释放张力以允许钎焊箔,线圈或环在其自身下被推靠在单元壁上 弹性。 然后将顶部和底部面板安装在靠近单元格边缘的芯上,以形成顶部和底部表面。 然后从面板向蜂窝芯材料施加压力。 然后将夹层结构的温度升高直到钎焊箔熔化。 毛细吸引导致现在的液体钎焊材料流入细胞节点之间的间隙以及蜂窝状核心细胞的相邻边缘和相邻的面板之间的间隙。
    • 9. 发明授权
    • Method of manufacturing an inflatable air inlet duct
    • 制造充气进气管道的方法
    • US4185373A
    • 1980-01-29
    • US922248
    • 1978-07-05
    • Charles L. HollandGeorge B. Nicoloff
    • Charles L. HollandGeorge B. Nicoloff
    • B64D33/02F42B15/00
    • F42B15/00B64D33/02B64D2033/0286Y10T29/4981
    • An air inlet duct for a jet propulsion missile or other vehicle which is movable between a housed, pre-launch position and an extended or deployed flight position. A method of manufacturing the duct is also disclosed. The duct system includes a flexible leading edge attached to a double-wall inflatable duct body. Drop threads extend between the duct body walls to hold an exact desired contour when the duct is inflated. A pivotable plate moves the inflatable duct between a housed, deflated, position and an inflated flight position. Manufacture of the inflatable duct is basically accomplished by preparing a foamed plastic form in the desired duct wall shape, covering the form with fabric, stitching through the foam and fabric, coating the fabric with a flexible sealing compound, dissolving away the foamed plastic and attaching the resulting inflatable duct to other missile components.
    • 用于喷气推进导弹或其他车辆的进气管道,其可在容纳的预发射位置和延伸或部署的飞行位置之间移动。 还公开了制造管道的方法。 管道系统包括连接到双壁可充气管道主体的柔性前缘。 当管道膨胀时,落纱线在管体壁之间延伸以保持精确期望的轮廓。 可枢转板将可充气管道移动到容纳的,放气的位置和充气的飞行位置之间。 充气管道的制造基本上通过制备所需导管壁形状的泡沫塑料形式,用织物覆盖形式,缝合穿过泡沫和织物,用柔性密封化合物涂覆织物,将泡沫塑料和附着物 所产生的充气管道与其他导弹部件。