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公开(公告)号：US20140263847A1
公开(公告)日：2014-09-18
申请号：US13804331
申请日：2013-03-14
摘要： Mechanisms for deploying a solar array include an elongated deployment member routed along a first panel, along an extension, and at least partially along a second panel. The elongated deployment member is configured to, upon retraction of the elongated deployment member by the deployment motor, move the extension into an extended position and rotate the second panel about a hub located at a distal end of the extension. Solar array assemblies include such a mechanism. Methods of deploying a solar array include retracting an elongated deployment member to rotate an extension into an extended position and further retracting the elongated deployment member to rotate a panel coupled to the extension approximately 360° about a hub of the extension.
摘要翻译： 用于部署太阳能阵列的机构包括沿着第一面板沿着延伸部沿着第二面板至少部分地布置的细长展开构件。 细长展开构件构造成在通过展开电机缩回细长展开构件时，将延伸部移动到延伸位置，并且使第二面板围绕位于延伸部的远端的毂旋转。 太阳能阵列组件包括这种机构。 部署太阳能阵列的方法包括缩回细长展开构件以将延伸部旋转到延伸位置，并且进一步缩回细长展开构件以使围绕延伸部的轮毂大约360°连接到延伸部的面板旋转。
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公开(公告)号：US20140263844A1
公开(公告)日：2014-09-18
申请号：US14198126
申请日：2014-03-05
申请人： The Boeing Company
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.
摘要翻译： 一种用于部署一组面板的方法和装置。 一种装置包括一组面对飞行器侧面的折叠构型的面板，连接到该组面板的一组柔性构件以及与该组面板和一组柔性构件相关联的界面系统。 所述接口系统被配置为当所述一组弹性构件从所述航天器延伸时将所述一组面板从所述折叠构型移动到展开配置。
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公开(公告)号：US08814099B1
公开(公告)日：2014-08-26
申请号：US13199430
申请日：2011-08-30
摘要： A Deployable Morphing Modular Solar Array (DMMSA) for deploying Deployable Morphing Modular Solar Power Assemblies (DMMSPAs) from a spacecraft is provided. The DMMSA comprises a Root Staging and Deployment Mechanism (RSDM) mounted to a spacecraft. A plurality of petal assemblies are rotatably secured to the RSDM with each petal assembly having at least DMMSPA secured thereon and each DMMSPA having a slight V-configuration. A launch restraint assembly stacks and sandwiches the petal assemblies prior to deployment with the launch restraint assembly pre-loading each petal assembly's one or more DMMSPA into a substantially flat configuration. Upon release of the launch restraint assembly, the stacked and sandwiched petal assemblies rotate relative to the spacecraft and each petal assemblies DMMSPA elastically morphs from the substantially flat configuration into the slight V-configuration.
摘要翻译： 提供了一种用于从航天器部署可部署变形模块化太阳能发电组件（DMMSPA）的可部署变形模块化太阳能阵列（DMMSA）。 DMMSA包括安装在航天器上的根分段和部署机制（RSDM）。 多个花瓣组件可旋转地固定到RSDM上，其中每个花瓣组件至少具有DMMSPA，并且每个DMMSPA具有轻微的V形构型。 发射约束装置在展开前利用发射约束装置在每个花瓣组件的一个或多个DMMSPA预加载到基本上平坦的构型中，堆叠并夹住花瓣组件。 在释放发射约束组件时，堆叠和夹持的花瓣组件相对于航天器旋转，并且每个花瓣组件DMMSPA从基本平坦的构型弹性变形成轻微的V形构型。
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94.发明申请Gyroless Three-Axis Sun Acquisition Using Sun Sensor and Unscented Kalman Filter 有权无陀螺三轴太阳采集采用Sun传感器和无卡尔曼滤波器公开(公告)号：US20140231589A1
公开(公告)日：2014-08-21
申请号：US14181492
申请日：2014-02-14
申请人： The Boeing Company
发明人： Tung-Ching Tsao , Richard Y. Chiang
CPC分类号： B64G1/363
摘要： An attitude estimator that uses sun sensor outputs as the only attitude determination measurements to provide three-axis attitude information. This is accomplished by incorporating the Euler equation into the estimator. An unscented Kalman filter is employed to accommodate various nonlinear characteristics and uncertainties of the spacecraft dynamics and thus improve the robustness and accuracy of the attitude estimate.
摘要翻译： 使用太阳传感器输出作为唯一姿态确定测量来提供三轴姿态信息的姿态估计器。 这通过将欧拉方程并入估计器来实现。 采用无色卡尔曼滤波器来适应航天器动力学的各种非线性特征和不确定性，从而提高姿态估计的鲁棒性和准确性。
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公开(公告)号：US08403270B2
公开(公告)日：2013-03-26
申请号：US11521672
申请日：2006-09-15
IPC分类号： B64G1/44
摘要： A method and apparatus for deploying a fixed and canted solar array of a satellite. The solar array is rotated in a first plane and about a first axis from a stowed position to a first position, rotated about a second axis orthogonal to the first axis from the first position to a deployed position determined by a deployment orbit of the satellite, and locked in the deployed position to prevent further motion of the solar array relative to a satellite body for the operational life of the satellite.
摘要翻译： 一种用于部署卫星的固定和倾斜太阳能阵列的方法和装置。 太阳能阵列在第一平面中旋转，并且围绕第一轴线从收起位置旋转到第一位置，从与第一位置正交的第二轴线从第一位置旋转到由卫星的展开轨道确定的展开位置， 并锁定在展开位置，以防止太阳能阵列相对于卫星的卫星进一步运动，从而达到卫星的使用寿命。
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公开(公告)号：US08242349B2
公开(公告)日：2012-08-14
申请号：US12145663
申请日：2008-06-25
申请人： Joseph P. Carroll
发明人： Joseph P. Carroll
摘要： A solar concentrator includes a plurality of separate panels positioned between opposed support rods. Tension elements extend between the support rods and mount the plurality of panels.
摘要翻译： 太阳能集中器包括定位在相对的支撑杆之间的多个分开的面板。 张力元件在支撑杆之间延伸并安装多个面板。
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公开(公告)号：US20110210209A1
公开(公告)日：2011-09-01
申请号：US13036910
申请日：2011-02-28
IPC分类号： B64G1/44 , B64G1/66 , B65H75/18 , H01L31/045
摘要： A deployable structure that may include a slit-tube longeron and a flat panel coupled with the slit-tube longeron. The slit-tube longeron may include a tubular member having a slit that runs along the longitudinal length of the slit-tube longeron. The deployable structure may be configured to couple with a satellite. And the deployable structure may be configured to transform between a stowed state and a deployed state where the tubular member is substantially straight when the deployable structure is in the deployed state, and the tubular member is wrapped around the satellite when the deployable structure is in the stowed state.
摘要翻译： 可展开的结构，其可以包括狭缝管长孔和与狭缝管连接的平板。 狭缝管长龙可以包括具有沿着狭缝管长孔的纵向长度延伸的狭缝的管状构件。 可部署结构可以被配置成与卫星耦合。 并且可部署结构可以被配置为在收起状态和展开状态之间转换，其中当展开结构处于展开状态时，管状构件基本上是直的，并且当可部署结构处于展开状态时，管状构件被包裹在卫星周围 收起状态
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公开(公告)号：US07980514B2
公开(公告)日：2011-07-19
申请号：US12048981
申请日：2008-03-14
申请人： James Wehner , Lael Rudd , Christian Harris , Shahram Foroozan
发明人： James Wehner , Lael Rudd , Christian Harris , Shahram Foroozan
CPC分类号： B64G1/506 , B64G1/283 , B64G1/285 , B64G1/407 , B64G1/428 , B64G1/44 , B64G1/443 , B64G1/66 , Y10S136/292
摘要： One embodiment of the invention includes a spacecraft. The spacecraft comprises at least one solar array panel comprising an array of solar cell sections. Each of the solar cell sections can be configured to generate electrical power from received solar radiation. The spacecraft also comprises a solar array selection controller configured to selectively deactivate a portion of the array of solar cell sections to generate a torque on the spacecraft based on a difference in at least one of solar and thermal radiation pressure between an activated portion of the array of solar cell sections and the deactivated portion of the array of solar cell sections.
摘要翻译： 本发明的一个实施例包括一个航天器。 宇宙飞船包括至少一个包括太阳能电池部分阵列的太阳能阵列面板。 每个太阳能电池部分可被配置为从接收的太阳辐射产生电力。 航天器还包括太阳能阵列选择控制器，该太阳能阵列选择控制器被配置为基于在阵列的激活部分之间的太阳能和热辐射压力中的至少一个的差异来选择性地停用太阳能电池部分阵列的一部分以在航天器上产生扭矩 的太阳能电池部分和太阳能电池部分阵列的失活部分。
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公开(公告)号：US20110011983A1
公开(公告)日：2011-01-20
申请号：US12873752
申请日：2010-09-01
申请人： Richard R. King , James H. Ermer , Peter C. Coller , Chris Fetzer
发明人： Richard R. King , James H. Ermer , Peter C. Coller , Chris Fetzer
IPC分类号： B64G1/44 , H01L31/0256 , H01L31/042 , H01L31/18 , H01L21/20
CPC分类号： H01L31/1844 , H01L31/036 , H01L31/0687 , H01L31/1852 , Y02E10/544 , Y02P70/521
摘要： The present invention provides a photovoltaic cell comprising a GaInP subcell comprising a disordered group-III sublattice, a Ga(In)As subcell disposed below the GaInP subcell, and a Ge substrate disposed below the Ga(In)As subcell comprising a surface misoriented from a (100) plane by an angle from about 8 degrees to about 40 degrees toward a nearest (111) plane.
摘要翻译： 本发明提供一种包括GaInP子电池的光伏电池，该GaInP子电池包括无序III族子晶格，设置在GaInP子电池下方的Ga（In）As子电池，以及设置在Ga（In）As子电池下方的Ge衬底， （100）平面朝向最近（111）面约8度至约40度的角度。
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公开(公告)号：US20100276547A1
公开(公告)日：2010-11-04
申请号：US12773036
申请日：2010-05-04
摘要： A low earth orbit system for beaming energy to earth includes a solar reflector that collects and focuses solar light onto a solar panel, transforming it into electricity to drive a diode pumped laser, which then produces a high-power laser beam that is directed to a receiver on the surface of the Earth via a diffractive lens. A steering system of optics and automated hardware controls the beam direction.
摘要翻译： 用于将能量发射到地球的低地球轨道系统包括太阳能反射器，其将太阳光聚集并聚焦到太阳能电池板上，将其转换成电以驱动二极管泵浦激光器，其然后产生被引导到 接收器通过衍射透镜在地球表面上。 光学和自动化硬件的转向系统控制光束方向。
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