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1. 发明申请

US20180226725A1 FOLDABLE RADIO WAVE ANTENNA DEPLOYMENT APPARATUS FOR A SATELLITE 审中-公开
公开(公告)号：US20180226725A1
公开(公告)日：2018-08-09
申请号：US15868710
申请日：2018-01-11
申请人： Cubic Corporation
发明人： William R. Clayton , Paul A. Gierow
IPC分类号： H01Q15/16
CPC分类号： H01Q15/161 , H01Q1/288 , H01Q19/132
摘要： The present disclosure describes an antenna that has a parabola-shaped, flexible reflector member and one or more radial ribs embedded in the flexible reflector member and arranged to bias the reflector member in an open state.

2. 发明申请

US20170222308A1 Deployable Reflector 审中-公开
公开(公告)号：US20170222308A1
公开(公告)日：2017-08-03
申请号：US15387437
申请日：2016-12-21
申请人： TENDEG LLC
发明人： Gregg E. Freebury , Neal J. Beidleman
IPC分类号： H01Q1/28 , H01Q5/30 , H01Q15/16
CPC分类号： H01Q1/288 , H01Q15/161
摘要： A reflector assembly including a truss engaging the first net at a first plurality of points along the first net perimeter edge and engaging a second net at a second plurality of points along the second net perimeter edge. A truss deployment assembly moves the truss between a truss stowed condition and a truss deployed condition, the truss in the truss deployed condition tensioning said first net or said second net to maintain a substantially flat or parabolic net outer surface. A reflector disposed at the first net sends or receives remote data.

3. 发明申请

US20170201031A1 ARTICLE AND METHOD OF FORMING AN ARTICLE 审中-公开
公开(公告)号：US20170201031A1
公开(公告)日：2017-07-13
申请号：US15400453
申请日：2017-01-06
申请人： THE SECANT GROUP, LLC
发明人： Todd J. GELB , Sean Christopher GLASBY , Daniel P. TREUSCH, Jr.
IPC分类号： H01Q15/16 , H01Q1/40 , H01Q1/28 , H01Q1/36 , H01Q13/02
CPC分类号： H01Q15/161 , H01Q1/288 , H01Q1/368 , H01Q1/40 , H01Q13/0283 , H01Q15/141 , H01Q15/168
摘要： A shape memory alloy article and method a deploying the article in deep space is provided. The shape memory alloy article may be an interlaced mesh structure. The article may be stored in a deformed configuration in a container for transport aboard a satellite or spacecraft. Upon reaching a desired location the article is removed from the container and heated to allow for transformation to an operating configuration.

4. 发明授权

US09637248B2 Component deployment system 有权
公开(公告)号：US09637248B2
公开(公告)日：2017-05-02
申请号：US14198126
申请日：2014-03-05
申请人： The Boeing Company
发明人： Hugh Quenten Cook, Jr. , Andrew R. Streett
IPC分类号： B64G1/24 , B64G1/22 , B64G1/44 , H01Q1/28 , H01Q1/08 , H02S30/20 , H01Q15/16 , B64G1/66
CPC分类号： B64G1/222 , B64G1/22 , B64G1/44 , B64G1/66 , H01Q1/08 , H01Q1/288 , H01Q15/161 , H02S20/30 , H02S30/20
摘要： A method and apparatus for deploying a group of panels. An apparatus comprises a group of panels in a folded configuration against a side of a spacecraft, a group of flexible members connected to the group of panels, and an interface system associated with the group of panels and the group of flexible members. The interface system is configured to move the group of panels from the folded configuration to a deployed configuration when the group of flexible members is extended from the spacecraft.

5. 发明授权

US09496621B2 Large deployable reflector for a satellite antenna 有权
标题翻译：用于卫星天线的大型部署式反射器
公开(公告)号：US09496621B2
公开(公告)日：2016-11-15
申请号：US14440515
申请日：2013-11-04
申请人： Thales Alenia Space Italia S.p.A. Con Unico Socio
发明人： Alberto Meschini , Riccardo Rigato , Davide Scarozza
IPC分类号： H01Q15/16 , B64G1/22 , H01Q1/28 , B64G1/66
CPC分类号： H01Q15/161 , B64G1/222 , B64G1/66 , H01Q1/288
摘要： A large deployable reflector for an antenna suitable for being installed on board a satellite and provided with a support structure, a parabolic mirror carried by the support structure and a connection arm for mounting the support structure on the satellite; the support structure being a jointed reticulate structure that is able to assume a compact inoperative stowed configuration and an operative deployed configuration and is composed of ‘n’ elements articulated to form tetrahedrons having respective triangular bases, which are connected to each other at the axial ends of respective first sides and have respective external vertices, which are opposite to said respective first sides and, when the reflector is arranged in the deployed configuration, ideally lie on a cone tangent to the parabolic mirror.
摘要翻译：适用于安装在卫星上并具有支撑结构的天线的大型可展开反射器，由支撑结构承载的抛物面镜和用于将支撑结构安装在卫星上的连接臂; 所述支撑结构是接合的网状结构，其能够采取紧凑的非操作的收起构型和可操作展开的构造，并且由铰链的“n”个元件组成，以形成具有各自的三角形基座的四面体，所述四面体在轴向端部彼此连接并且具有与所述相应的第一侧相对的各自的外部顶点，并且当反射器布置在展开构造中时，理想地位于与抛物面镜相切的锥体上。

6. 发明授权

US09084319B2 Circuits and methods for reducing flicker in an LED light source 有权
标题翻译：降低LED光源闪烁的电路和方法
公开(公告)号：US09084319B2
公开(公告)日：2015-07-14
申请号：US13667964
申请日：2012-11-02
申请人： Texas Instruments Incorporated
发明人： Timothy Roy Sullivan , Daniel Ross Herrington
IPC分类号： H05B37/00 , H05B39/00 , H05B41/14 , H05B33/08
CPC分类号： B64G1/222 , B64G1/44 , B64G1/66 , H01Q1/08 , H01Q1/288 , H01Q15/161 , H02S30/20 , H05B33/0815 , H05B33/0845 , H05B33/0848
摘要： Method and circuits for balancing a first waveform used to drive an LED are disclosed herein. The first waveform has a first cycle with a first amplitude and a second cycle with a second amplitude. An embodiment of the method includes adjusting the first amplitude of the first cycle to match the second amplitude of the second cycle, the result being a second waveform. The LED is driven with the second waveform.
摘要翻译：本文公开了用于平衡用于驱动LED的第一波形的方法和电路。第一波形具有具有第一幅度的第一周期和具有第二幅度的第二周期。该方法的实施例包括调整第一周期的第一幅度以匹配第二周期的第二幅度，其结果为第二波形。 LED以第二波形驱动。

7. 发明申请

US20150194733A1 MESH REFLECTOR WITH TRUSS STRUCTURE 有权
标题翻译：具有TRUSS结构的反射器
公开(公告)号：US20150194733A1
公开(公告)日：2015-07-09
申请号：US14151514
申请日：2014-01-09
申请人： MEHRAN MOBREM , GEOFFREY W. MARKS
发明人： MEHRAN MOBREM , GEOFFREY W. MARKS
IPC分类号： H01Q15/16 , G02B7/182 , G02B5/10
CPC分类号： H01Q15/168 , G02B5/10 , G02B7/182 , H01Q1/288 , H01Q15/161
摘要： A reflector assembly includes a frame centered about a longitudinal axis and having a first height along the axis. A curved body extends from the frame and has a second height along the longitudinal axis could be greater than the first height. A stretchable membrane has an electromagnetically reflective surface and is secured to the curved body.
摘要翻译：反射器组件包括围绕纵向轴线居中并具有沿轴线的第一高度的框架。从框架延伸并且沿着纵向轴线具有第二高度的弯曲体可以大于第一高度。可拉伸膜具有电磁反射表面并固定到弯曲体上。

8. 发明申请

US20150151854A1 DEPLOYABLE TENSEGRITY STRUCTURE, ESPECIALLY FOR SPACE APPLICATIONS 有权
标题翻译：可应用的灵敏度结构，特别适用于空间应用
公开(公告)号：US20150151854A1
公开(公告)日：2015-06-04
申请号：US14386095
申请日：2012-03-19
申请人： Lucio Gerardo Scolamiero , Valfredo Zolesi , Plei Luigi Ganga , Paolo Podio-Guidugli , Gunnar Tibert , Andren Micheletti
发明人： Lucio Gerardo Scolamiero , Valfredo Zolesi , Plei Luigi Ganga , Paolo Podio-Guidugli , Gunnar Tibert , Andren Micheletti
IPC分类号： B64G1/22
CPC分类号： B64G1/222 , H01Q1/288 , H01Q15/161
摘要： A deployable structure comprises a first and second flexible tension members respectively defining a first and second contours of a ring. A first plurality of rigid compression members extends between the first and second contours. Only one end of each first plurality compression member is mounted on the first contour. A second plurality of rigid compression members extends between the first and second contours. Only one end of each second plurality compression member is mounted on the second contour. The first and second plurality of compression members are arranged with a repetitive crossing pattern around the ring. A first plurality of flexible tension members link each end of a compression member mounted on one of said contours to an end of another non-mounted compression member and a second plurality of flexible tension members link each end of a non-mounted compression member to an end of another non-mounted compression member.
摘要翻译：可部署结构包括分别限定环的第一和第二轮廓的第一和第二柔性张紧构件。第一多个刚性压缩构件在第一和第二轮廓之间延伸。每个第一多个压缩构件的仅一端安装在第一轮廓上。第二多个刚性压缩构件在第一和第二轮廓之间延伸。每个第二多个压缩构件的仅一端安装在第二轮廓上。第一和第二多个压缩构件以围绕环的重复交叉图案布置。第一多个柔性张紧构件将安装在一个所述轮廓上的压缩构件的每个端部连接到另一个未安装的压缩构件的端部，并且第二多个柔性张紧构件将非安装的压缩构件的每个端部连接到另一个未安装的压缩构件的端部。

9. 发明授权

US08800935B2 Spacecraft payload positioning with respect to a virtual pivot point 有权
标题翻译：相对于虚拟枢轴点的航天器有效载荷定位
公开(公告)号：US08800935B2
公开(公告)日：2014-08-12
申请号：US13044278
申请日：2011-03-09
申请人： Colin M. Francis
发明人： Colin M. Francis
IPC分类号： B64G1/22
CPC分类号： H01Q15/161 , B64G1/222 , B64G1/66 , H01Q1/288 , Y10T74/20
摘要： 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.
摘要翻译：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。

10. 发明授权

US08789796B2 High capacity broadband satellite 有权
标题翻译：高容量宽带卫星
公开(公告)号：US08789796B2
公开(公告)日：2014-07-29
申请号：US13101944
申请日：2011-05-05
申请人： Joel Francis Boccio , Gerrit Van Ommering , Walter S. Gelon , Steven Daniel Perez , Eric V. Werner
发明人： Joel Francis Boccio , Gerrit Van Ommering , Walter S. Gelon , Steven Daniel Perez , Eric V. Werner
IPC分类号： B64G1/22 , B64G1/66
CPC分类号： H01Q1/288 , B64G1/1007 , B64G1/222 , B64G1/641 , B64G1/66 , H01Q1/08 , H01Q15/161 , H01Q19/132
摘要： A high capacity broadband service is provided from an Earth orbiting satellite having a payload that includes multiple large antennas, the satellite having an inverted configuration when deployed on orbit. The satellite has an aft surface proximate to a launch vehicle structural interface, a forward surface opposite to said aft surface, and a structure disposed therebetween. In a launch configuration, two or more deployable antennas are disposed, undeployed, on or proximate to and forward of the forward surface; on-orbit, the payload is operable when the satellite is disposed with the aft surface substantially Earth facing while the forward surface is substantially facing in an anti-Earth direction. Each deployable antenna is disposed, so as to be Earth facing, when deployed, in a position substantially forward and outboard of the forward surface.
摘要翻译：来自具有包括多个大天线的有效载荷的地球轨道卫星提供高容量宽带服务，该卫星在部署在轨道上时具有倒置配置。卫星具有靠近运载火箭结构界面的后表面，与所述后表面相对的前表面，以及设置在其间的结构。在发射配置中，两个或多个可展开的天线被放置在前表面上或靠近和向前的前表面上，未被部署; 在轨道上，当卫星被设置成具有大致面向地面的后表面时，有效载荷可操作，同时前表面基本上面向反地球方向。每个可部署的天线被布置成在部署时面向地面，位于前表面的大致向前和向外的位置。

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