公开(公告)号：US20230348112A1

公开(公告)日：2023-11-02

申请号：US18014870

申请日：2021-07-02

申请人： AIRBUS DEFENCE AND SPACE SAS

发明人： Florian GACOIN ,  Jean-Marc PIERINET ,  Mireya JOYA ,  Julien PRADAL ,  Sara LOPEZ-SANCHEZ ,  Nicolas FABRE

IPC分类号： B64G1/10 ,  B64G1/66

CPC分类号： B64G1/10 ,  B64G1/66 ,  B64G2001/228

摘要： A primary structure (100) for a spacecraft (200) including an interface ring (10) and a predetermined number of panels defining a box arranged to close an interior volume of the spacecraft. The box is connected to the interface ring. Side panels of the box are parallel to a geometric axis (A) of the interface ring, the interface ring is temporarily fastened to a system supporting the spacecraft in a launcher. Each panel is a one-piece panel formed by machining a metal material. The side panels at the base of the box are connected to the interface ring (10) via damping inserts (60).

公开(公告)号：US11802606B2

公开(公告)日：2023-10-31

申请号：US16877480

申请日：2020-05-18

申请人： The Boeing Company

发明人： Richard W. Aston ,  Matthew Joseph Herrmann ,  Christopher David Joe ,  Manav Hemal Sanghvi

IPC分类号： B64G1/64 ,  F16F15/08 ,  F16M13/02 ,  B64G1/22

CPC分类号： F16F15/08 ,  B64G1/641 ,  B64G1/645 ,  F16M13/02 ,  B64G2001/228

摘要： A vibration isolation system is disclosed, including a rigid retaining device having an internal space, a first external side, and a second external side. A rigid anchoring device is retained in the internal space of the rigid retaining device. The anchoring device has a linkage member that extends from the internal space to the first external side of the retaining device and is configured for rigid connection to a first apparatus. The second side of the retaining device is configured for attachment to a second apparatus. A damping material is sandwiched between the retaining device and the anchoring device, and is configured to limit transfer of vibration between the retaining device and the anchoring device.

公开(公告)号：US09752644B2

公开(公告)日：2017-09-05

申请号：US15101657

申请日：2014-12-02

申请人： KOREA AEROSPACE RESEARCH INSTITUTE

发明人： Dae Kwan Kim ,  Hong-Taek Choi

IPC分类号： F16M13/00 ,  F16F15/08 ,  F16M11/22 ,  B64G1/22

CPC分类号： F16F15/08 ,  B64G2001/228 ,  F16M11/22 ,  F16M2200/08

摘要： Provided is a non-adhesive type vibration reduction apparatus comprising: a support; a body; and an elastomer, wherein the elastomer is coupled in a non-adhesive manner in which an adhesive is not used, thereby preventing a separation of and reducing a damage of an elastomer which result from a weakening of an adhesive force.

公开(公告)号：US09567109B2

公开(公告)日：2017-02-14

申请号：US14488902

申请日：2014-09-17

申请人： The Boeing Company

发明人： Thomas E. Robles ,  Trevor Scott Howard

IPC分类号： B64G1/64 ,  B64G1/00 ,  B64G1/10 ,  B64G1/22

CPC分类号： B64G1/005 ,  B64G1/10 ,  B64G1/64 ,  B64G1/641 ,  B64G2001/228

摘要： A method and apparatus for deploying a space structure. The space structure is secured to a base with release mechanisms that engage features of the space structure when the base is in a first position. The base is moved from the first position to a second position to deploy the space structure. The release mechanisms are moved at substantially a same time to disengage from the features and release the space structure from the base without imparting a transverse load to the space structure when the base moves from the first position towards the second position to deploy the space structure.

摘要翻译： 一种用于部署空间结构的方法和装置。 当基座处于第一位置时，空间结构被固定到具有释放机构的底座，释放机构接合空间结构的特征。 基座从第一位置移动到第二位置以部署空间结构。 当基座从第一位置朝向第二位置移动以展开空间结构时，释放机构基本上同时移动以与特征脱离并且从基座释放空间结构而不向空间结构施加横向负载。

公开(公告)号：US20160257433A1

公开(公告)日：2016-09-08

申请号：US15059411

申请日：2016-03-03

申请人： York Space Systems LLC

发明人： Dirk WALLINGER

IPC分类号： B64G1/22 ,  B64G1/66 ,  B64G1/10

CPC分类号： B64G1/66 ,  B64G1/002 ,  B64G1/10 ,  B64G1/50 ,  B64G1/503 ,  B64G1/641 ,  B64G2001/228 ,  H05K7/20218 ,  H05K7/20245 ,  H05K7/203

摘要： A compartment for a space vehicle includes a pressurized structure having a structural wall, the structural wall having interior surfaces facing an interior of the compartment and exterior surfaces exposed to an external environment. An internal mounting structure for mounting a component is provided within the compartment, and mounting features support the internal mounting structure from the pressurized structure. The internal mounting structure is spaced away from the interior surfaces of the pressurized structure, and a thermal fluid is provided in the pressurized structure. The thermal fluid enables convective heat transfer between the component mounted on the internal mounting structure and the interior surfaces of the pressurized structure.

摘要翻译： 用于空间车辆的隔间包括具有结构壁的加压结构，所述结构壁具有面向隔室内部的内表面和暴露于外部环境的外表面。 用于安装部件的内部安装结构设置在隔间内，并且安装特征从加压结构支撑内部安装结构。 内部安装结构与加压结构的内表面间隔开，并且在加压结构中设置热流体。 热流体使得能够在安装在内部安装结构上的部件与加压结构的内表面之间进行对流传热。

公开(公告)号：US20140084113A1

公开(公告)日：2014-03-27

申请号：US13626843

申请日：2012-09-25

申请人： HONEYWELL INTERNATIONAL INC.

发明人： Tim Daniel Barber ,  Ken Young ,  Timothy Hindle

IPC分类号： B64G1/66

CPC分类号： B64G1/641 ,  B64G1/283 ,  B64G1/285 ,  B64G1/286 ,  B64G2001/228

摘要： Launch lock assemblies with reduced preload are provided. The launch lock assembly comprises first and second mount pieces, a releasable clamp device, and a pair of retracting assemblies. Each retracting assembly comprises a pair of toothed members having interacting toothed surfaces. The releasable clamp device normally maintains the first and second mount pieces in clamped engagement. When the releasable clamp device is actuated, the first and second mount pieces are released from clamped engagement and one toothed member of each retracting assembly moves in an opposite direction relative to the other one toothed member of the other retracting assembly to define an axial gap on each side of the first mount piece.

摘要翻译： 提供减少预载的启动锁组件。 发射锁定组件包括第一和第二安装件，可释放的夹紧装置和一对缩回组件。 每个缩回组件包括具有相互作用的齿形表面的一对齿形构件。 可释放的夹紧装置通常将第一和第二安装件保持在夹紧的接合状态。 当可释放的夹紧装置被致动时，第一和第二安装件从夹紧的接合中释放，并且每个缩回组件的一个齿形构件相对于另一个缩回组件的另一个齿形构件在相反的方向上移动以限定一个轴向间隙 第一个安装件的每一侧。

公开(公告)号：US08532847B1

公开(公告)日：2013-09-10

申请号：US13629671

申请日：2012-09-28

申请人： Fukashi Andoh

发明人： Fukashi Andoh

IPC分类号： G06F17/10

CPC分类号： F16F15/002 ,  B64G1/52 ,  B64G1/641 ,  B64G2001/228

摘要： A vibration suppressing device for a spacecraft. A plurality of spacecraft deflection sensors measure a plurality of spacecraft deflections at specified locations on a spacecraft structure. A spacecraft modal coordinate calculation unit calculates a plurality of spacecraft modal coordinates. A high pass filter extracts a plurality of fluctuations of spacecraft modal coordinates. A cost function calculation unit calculates a cost function as a function of the plurality of fluctuations of spacecraft modal coordinates. A payload position calculation unit calculates an optimal payload position minimizing the cost function. A payload position adjustment device generates a control input suppressing a vibration transmitted to the payload system, and adjusts the payload position to the optimal payload position.

摘要翻译： 一种用于航天器的振动抑制装置。 多个航天器偏转传感器测量在航天器结构上的特定位置处的多个航天器偏转。 航天器模态坐标计算单元计算多个航天器模态坐标。 高通滤波器提取了航天器模态坐标的多个波动。 成本函数计算单元根据航天器模态坐标的多个波动来计算成本函数。 有效载荷位置计算单元计算最小化成本函数的最优有效载荷位置。 有效负载位置调整装置产生抑制传输到有效载荷系统的振动的控制输入，并将有效载荷位置调整到最佳有效载荷位置。

公开(公告)号：US07234663B1

公开(公告)日：2007-06-26

申请号：US11152529

申请日：2005-06-14

申请人： John E. Higgins

发明人： John E. Higgins

IPC分类号： B64C1/40

CPC分类号： B64G1/002 ,  B64G2001/228 ,  G10K11/16

摘要： A launch vehicle payload fairing incorporating hollow cavities filled with an aerated fluid for the reduction of acoustic noise during launch. The fairing may also include a fluid ejection system for subsequent weight reduction.

摘要翻译： 一种运载火箭有效载荷整流装置，其中装有充满气体的空心腔，用于在发射期间减少噪音。 整流罩还可以包括用于随后减轻重量的流体喷射系统。

公开(公告)号：US06834841B2

公开(公告)日：2004-12-28

申请号：US10189860

申请日：2002-07-03

申请人： David A. Osterberg

发明人： David A. Osterberg

IPC分类号： F16M100

CPC分类号： F16F15/022 ,  B64G1/641 ,  B64G1/645 ,  B64G2001/228 ,  F16C32/044 ,  F16C2326/47

摘要： A method and system for calculating a control function for a structural system (10) that can be used to determine an appropriate control force to apply to an active member (18) within a stationary member (12) on the structural system (10). An active member (18) and a stationary member (12) are defined as a two-mass system in which the active member (18) and the stationary member (12) move in opposite directions. The stationary member (12) is mounted to an isolation subsystem (14) that is composed of six isolators (28) at multiple degrees of freedom. The isolation subsystem (14) is softer than the stationary member (12), active member (18) and a spacecraft surface (16) due to a damping element (32) of the isolation subsystem (16). The isolation subsystem (16) is mounted to the spacecraft (16) and decouples the spacecraft (16) from the stationary member (12) and thus the active member (18). An accurate control force for the active member (18) can be determined based upon the above structure (10).

摘要翻译： 一种用于计算结构系统（10）的控制功能的方法和系统，所述结构系统（10）可用于确定施加到结构系统（10）上的固定构件（12）内的有效构件（18）的适当控制力。 活动构件（18）和固定构件（12）被定义为活动构件（18）和固定构件（12）沿相反方向移动的双质量系统。 固定构件（12）安装到由多个自由度的六个隔离器（28）组成的隔离子系统（14）。 隔离子系统（14）由于隔离子系统（16）的阻尼元件（32）而比固定构件（12），有源构件（18）和航天器表面（16）软。 隔离子系统（16）被安装到航天器（16）并且将航天器（16）与固定构件（12）和所述有源构件（18）分离。 可以基于上述结构（10）来确定活动构件（18）的精确控制力。

公开(公告)号：US20030141416A1

公开(公告)日：2003-07-31

申请号：US10060439

申请日：2002-01-30

发明人： Kenneth N. Telford

IPC分类号： B64G001/10

CPC分类号： B64G1/645 ,  B64G1/641 ,  B64G2001/228

摘要： A variable spacer includes a plate having a first surface and a second surface. At least one hole is integrally formed within the plate, extending from the first surface to the second surface. The hole receives a shaft of a separation bolt used for attaching a spacecraft to a launch vehicle. The plate increases a first load within the separation bolt to a second load during a turbulent stage. The second load reduces a gapping that occurs between the launch vehicle and the spacecraft. Thereafter, the plate reduces the second load within the separation bolt to a third load during a separation stage. The third load decreases a shock level experienced by the spacecraft and the launch vehicle.

摘要翻译： 可变间隔件包括具有第一表面和第二表面的板。 至少一个孔一体地形成在板内，从第一表面延伸到第二表面。 该孔容纳用于将航天器附接到运载火箭的分离螺栓的轴。 在湍流阶段，板将分离螺栓内的第一负载增加到第二负载。 第二个负载减少了在运载火箭和航天器之间发生的间隙。 此后，在分离阶段期间，板将分离螺栓内的第二负载减小到第三负载。 第三负载降低了航天器和运载火箭所经历的冲击水平。