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    • 8. 发明授权
    • Linkage mechanism for a dual-motor lifting recliner
    • 双电动提升斜倚器的联动机构
    • US08944498B2
    • 2015-02-03
    • US13344330
    • 2012-01-05
    • Gregory M. Lawson
    • Gregory M. Lawson
    • A47C1/035
    • A61G5/14A47C1/0355F04C2270/041Y10T74/20
    • A seating unit that includes a linkage mechanism adapted to move the seating unit between closed, extended, reclined, and seat-lift positions is provided. The linkage mechanism includes a footrest assembly and a back-mounting link coupled to a seat-mounting plate, a base plate coupled to a lift-base assembly via a lift assembly, a drive bracket, a motor tube, and two linear actuators for automating adjustment of the linkage mechanism. In operation, a first phase involves a second linear actuator rotating the motor tube, thereby causing the seat-adjustment assembly to bias the seat-mounting plate. A second phase involves a first linear actuator rotating the drive bracket, thereby causing the footrest assembly to extend or retract without affecting the bias of the back-mounting link. A third phase involves the first linear actuator causing the lift assembly to raise and tilt the base plate directly over the lift-base assembly.
    • 提供一种座椅单元,其包括适于将座椅单元移动到关闭的,延伸的,倾斜的和座椅升降位置之间的联动机构。 联动机构包括:脚踏组件和联接到座椅安装板的后部安装连杆,通过提升组件联接到升降台组件的基板,驱动支架,马达管和用于自动化的两个线性致动器 调整联动机制。 在操作中,第一阶段涉及旋转电动机管的第二线性致动器,从而使座椅调节组件偏置座椅安装板。 第二阶段涉及旋转驱动支架的第一线性致动器,从而使脚踏组件能够延伸或缩回,而不影响后安装连杆的偏压。 第三阶段涉及第一线性致动器,其使升降组件升高并将基板倾斜到升降台组件的正上方。
    • 10. 发明授权
    • Spacecraft payload positioning with respect to a virtual pivot point
    • 相对于虚拟枢轴点的航天器有效载荷定位
    • US08800935B2
    • 2014-08-12
    • US13044278
    • 2011-03-09
    • Colin M. Francis
    • Colin M. Francis
    • B64G1/22
    • H01Q15/161B64G1/222B64G1/66H01Q1/288Y10T74/20
    • A spacecraft payload element is rotated by a mechanism about virtual pivot point (VPP) substantially distant from the mechanism. The mechanism couples the payload element to a spacecraft main body structure, and has a four-bar linkage configured to rotate the payload element about a virtual pivot point (VPP). The VPP may be proximate to the focus or center of gravity (cg) of the payload element. Rotation of the payload element about the VPP may be controlled by linear or rotary actuators which drive the four-bar linkage. The four-bar linkage may be configured to provide a mechanical advantage to the actuator.
    • 航天器有效载荷元件通过与该机构基本上远的虚拟枢轴点(VPP)的机构旋转。 该机构将有效载荷元件耦合到航天器主体结构,并且具有配置成围绕虚拟枢轴点(VPP)旋转有效载荷元件的四杆连杆。 VPP可以接近有效载荷元件的焦点或重心(cg)。 关于VPP的有效载荷元件的旋转可以由驱动四杆连杆的线性或旋转致动器来控制。 四杆联动装置可被配置成为致动器提供机械优点。