公开(公告)号：EP0957288A3

公开(公告)日：2002-11-27

申请号：EP99109105.9

申请日：1999-05-07

申请人： TRW Inc.

发明人： Shtarkman, Emil M. ,  Doherty, Kathleen M. ,  Parker, A. Dale

IPC分类号： F16F15/00

CPC分类号： F16F15/005 ,  F16F9/53 ,  F16F15/03 ,  H01Q1/005 ,  H01Q1/288

摘要： A vibration control system is provided for an appendage such as an antenna 10 coupled to a platform such as a spacecraft 12. The antenna 10 is coupled at a base 14 so as to extend from the spacecraft 12. A plurality of guidelines 20 extend between remote portions 22 of the antenna 10 and the antenna base 14. A plurality of motion control elements 36 are provided within the antenna structure for reducing oscillation settling time of the antenna 10 relative to the spacecraft 12. The motion control elements 36 include a material disposed therein having its damping response changed according to the magnitude of an electric or magnetic field applied thereto.

公开(公告)号：EP1017115A2

公开(公告)日：2000-07-05

申请号：EP99124054.0

申请日：1999-12-09

申请人： TRW INC.

发明人： Triller, Michael J. ,  Doherty, Kathleen M. ,  Felts, Christopher W. ,  Hill, Lisa R. ,  Lavinsky, Craig A.

IPC分类号： H01L41/053

CPC分类号： H01L41/08 ,  H01L41/053 ,  H01L41/0533

摘要： A singly or doubly encapsulated actuator/sensor package in which a ceramic actuator/sensor (10) may be first encapsulated in a primary encapsulating material (12) and is encapsulated in a fiber-reinforced composite material (20, 22). A combination of the material and lay-up angles (θ) of the fiber-reinforced composite material (20, 22) are used to control selection of a composite coefficient of thermal expansion (CTE) and the stiffness or compliance of the package with respect to a selected axis. By optimal selection of the material and the lay-up angle, based upon a suitable actuation strength figure of merit, a CTE of zero or a CTE matching that of an underlying structural member (24) is obtained, while simultaneously maximizing the actuation strength in a selected actuation direction. Application of the invention to precision structures permits the underlying structures to be designed with very low stiffness, because precise, thermally stable, pointing or shaping actuation forces may be obtained in a thermally stable manner.

摘要翻译： 单个或双重封装的致动器/传感器封装，其中陶瓷致动器/传感器（10）可以首先封装在初级封装材料（12）中并被封装在纤维增强复合材料（20,22）中。 使用纤维增强复合材料（20,22）的材料和叠层角度（＆amp;重量）的组合来控制复合热膨胀系数（CTE）的选择以及包装的刚度或顺应性 相对于选定的轴。 通过优选选择材料和叠层角度，基于合适的致动强度品质因数，获得与下面的结构件（24）的CTE匹配的零或CTE的CTE，同时最大化驱动强度 选择的致动方向。 将本发明应用于精密结构允许底层结构被设计成具有非常低的刚度，因为可以以热稳定的方式获得精确的，热稳定的，指向或成形的致动力。

公开(公告)号：EP0957288A2

公开(公告)日：1999-11-17

申请号：EP99109105.9

申请日：1999-05-07

申请人： TRW Inc.

发明人： Shtarkman, Emil M. ,  Doherty, Kathleen M. ,  Parker, Dale A.

IPC分类号： F16F15/00

CPC分类号： F16F15/005 ,  F16F9/53 ,  F16F15/03 ,  H01Q1/005 ,  H01Q1/288

摘要： A vibration control system is provided for an appendage such as an antenna 10 coupled to a platform such as a spacecraft 12. The antenna 10 is coupled at a base 14 so as to extend from the spacecraft 12. A plurality of guidelines 20 extend between remote portions 22 of the antenna 10 and the antenna base 14. A plurality of motion control elements 36 are provided within the antenna structure for reducing oscillation settling time of the antenna 10 relative to the spacecraft 12. The motion control elements 36 include a material disposed therein having its damping response changed according to the magnitude of an electric or magnetic field applied thereto.

摘要翻译： 为诸如耦合到诸如航天器12的平台的天线10提供振动控制系统。天线10在基座14处被联接以便从航天器12延伸。多个准则20在遥控器 天线10的部分22和天线基座14.多个运动控制元件36设置在天线结构内，用于减少天线10相对于航天器12的振荡稳定时间。运动控制元件36包括设置在天线10内的材料 其阻尼响应根据施加到其上的电场或磁场的大小而改变。