AIRCRAFT MULTI-AXIS MODAL SUPPRESSION SYSTEM
    11.
    发明申请
    AIRCRAFT MULTI-AXIS MODAL SUPPRESSION SYSTEM 有权
    飞机多轴模式抑制系统

    公开(公告)号:US20060237594A1

    公开(公告)日:2006-10-26

    申请号:US11180309

    申请日:2005-07-12

    IPC分类号: G05D1/00

    CPC分类号: B64C13/16 B64C2220/00

    摘要: Vibrations due to excitation of the natural modes of an aircraft's body are suppressed by an active multi-axis modal suppression system. Dedicated sensors are positioned in the aircraft at optimal locations for sensing modal induced vibrations. The sensor produced signals are processed through control logic which, in response thereto, and in response to aircraft inertial, velocity and altitude related signals produces output control signals. The control signals effect control surface deployment creating forces to suppress the natural mode induced vibrations on multiple geometric axis's. More particularly, symmetric and anti-symmetric control surface deployments are used on one or more geometric axis's to damp lateral, longitudinal, vertical and most importantly torsional vibrational modes.

    摘要翻译: 通过主动多轴模态抑制系统抑制由于飞机身体的自然模式的激发引起的振动。 专用传感器位于飞行器的最佳位置,用于感测模态诱发的振动。 传感器产生的信号通过控制逻辑进行处理,响应于此,响应于飞机惯性,速度和高度相关的信号产生输出控制信号。 控制信号影响控制表面部署,产生力以抑制多个几何轴上的自然模式引起的振动。 更具体地说,在一个或多个几何轴上使用对称和反对称的控制表面布置以阻止侧向,纵向,垂直和最重要的扭转振动模式。