公开(公告)号：EP1010916A2

公开(公告)日：2000-06-21

申请号：EP99124099.5

申请日：1999-12-13

申请人： TRW INC.

发明人： Triller, Michael J. ,  Elliott, Lee E.

IPC分类号： F16F15/00

CPC分类号： F16F15/005 ,  Y10T29/42 ,  Y10T29/49622 ,  Y10T29/49771 ,  Y10T29/53039

摘要： A process for designing spacecraft structural elements (20, 30) that increases spacecraft structure intrinsic damping to relax stiffness design constraints that are necessary for precision pointing requirements. The process includes specifically designing the spacecraft structural elements (20, 30) to have a stiffness that is intrinsically not suitable to meet mission pointing performance requirements in order to reduce weight and volume. To overcome this deficiency, the structural elements (20, 30) are equipped with strain energy control elements (44) that sense strain in the structural elements (20, 30) from on-board and external disturbances, and provide actuation of the structural elements (20, 30) to counteract the sensed strain. The strain energy control elements (44) can be any suitable control element that senses strain and actuates the structural element (20, 30), such as piezoelectric electric or electrostrictive control elements. By reducing the stiffness requirements of the structural elements (20, 30), the control elements (44) can more readily provide a desired actuation for damping purposes in order to meet pointing performance requirements, and thus the weight and volume of the structural elements (20, 30) can be reduced over those known in the art. Relaxing the stiffness requirements of the structural elements (20, 30) allows the structural element (20, 30) to be made of materials having higher strength properties, instead of higher stiffness properties, thus allowing the structural element (20, 30) to meet the strength requirements to survive launch and deployment loads.

摘要翻译： 一种设计航天器结构元件（20,30）的过程，其增加航天器结构固有阻尼以放松精确指向要求所必需的刚度设计约束。 该过程包括具体设计航天器结构元件（20,30）以具有本质上不适合于任务指向性能要求的刚度以减小重量和体积。 为了克服该缺陷，结构元件（20,30）配备有应变能量控制元件（44），该应变能量控制元件（44）从板上和外部干扰中感测结构元件（20,30）中的应变，并且提供结构元件 （20,30）以抵消感测到的应变。 应变能量控制元件（44）可以是感测应变并致动结构元件（20,30）的任何合适的控制元件，例如压电或电致伸缩控制元件。 通过降低结构元件（20,30）的刚度要求，控制元件（44）可以更容易地提供用于减振目的的期望致动，以便满足指向性能要求，并因此满足结构元件（20,30）的重量和体积 20，30）可以比本领域已知的那些减少。 放宽结构元件（20,30）的刚度要求允许结构元件（20,30）由具有较高强度特性的材料制成，而不是较高的刚度特性，从而允许结构元件（20,30）符合 在发射和部署负载中存活的强度要求。

公开(公告)号：EP1010916A3

公开(公告)日：2000-09-20

申请号：EP99124099.5

申请日：1999-12-13

申请人： TRW INC.

发明人： Triller, Michael J. ,  Elliott, Lee E.

IPC分类号： F16F15/00 ,  B64G1/22

CPC分类号： F16F15/005 ,  Y10T29/42 ,  Y10T29/49622 ,  Y10T29/49771 ,  Y10T29/53039

摘要： A process for designing spacecraft structural elements (20, 30) that increases spacecraft structure intrinsic damping to relax stiffness design constraints that are necessary for precision pointing requirements. The process includes specifically designing the spacecraft structural elements (20, 30) to have a stiffness that is intrinsically not suitable to meet mission pointing performance requirements in order to reduce weight and volume. To overcome this deficiency, the structural elements (20, 30) are equipped with strain energy control elements (44) that sense strain in the structural elements (20, 30) from on-board and external disturbances, and provide actuation of the structural elements (20, 30) to counteract the sensed strain. The strain energy control elements (44) can be any suitable control element that senses strain and actuates the structural element (20, 30), such as piezoelectric electric or electrostrictive control elements. By reducing the stiffness requirements of the structural elements (20, 30), the control elements (44) can more readily provide a desired actuation for damping purposes in order to meet pointing performance requirements, and thus the weight and volume of the structural elements (20, 30) can be reduced over those known in the art. Relaxing the stiffness requirements of the structural elements (20, 30) allows the structural element (20, 30) to be made of materials having higher strength properties, instead of higher stiffness properties, thus allowing the structural element (20, 30) to meet the strength requirements to survive launch and deployment loads.

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。