公开(公告)号：US20060038082A1

公开(公告)日：2006-02-23

申请号：US11151908

申请日：2005-06-14

申请人： Mark Barton ,  Jonathon Miller

发明人： Mark Barton ,  Jonathon Miller

IPC分类号： B64G1/52

CPC分类号： B64G1/506

摘要： A thermal management system for a spacecraft module includes a baseplate and wall system that is precharacterized to provide a given level of thermal performance regardless of an orientation of the spacecraft relative to a source of solar energy. The system is characterized at a worst-case hot orientation, and at a worst-case cold orientation. The characterization provides a maximum temperature and a minimum temperature of components mounted on the baseplate as a function of the height of the walls. The height of the walls is selected to provide a suitable temperature range for the components, based on the power dissipation of the components. The system is designed to be symmetric, so that this temperature range is assured regardless of the orientation of the spacecraft.

摘要翻译： 用于航天器模块的热管理系统包括基板和壁系统，该基板和壁系统具有预特性以提供给定水平的热性能，而不管航天器相对于太阳能源的取向如何。 该系统的特征在于最坏情况下的热定向，并且处于最坏情况下的冷定向。 表征提供了作为墙壁高度的函数的安装在基板上的部件的最高温度和最小温度。 基于部件的功率耗散，选择壁的高度以为部件提供合适的温度范围。 该系统被设计为对称的，使得无论航天器的方向如何，该温度范围都是有保证的。

公开(公告)号：US08146867B2

公开(公告)日：2012-04-03

申请号：US11151906

申请日：2005-06-14

申请人： Luis G. Jordan ,  Thomas W. Vaneck ,  Scott A. McDermott ,  Jonathon Miller ,  Simon Morris Shand Weiss ,  Robert A. Summers

发明人： Luis G. Jordan ,  Thomas W. Vaneck ,  Scott A. McDermott ,  Jonathon Miller ,  Simon Morris Shand Weiss ,  Robert A. Summers

IPC分类号： B64G1/22

CPC分类号： B64G1/10 ,  B64G1/428 ,  B64G2001/1092

摘要： A spacecraft architecture and accompanying standard allows for the creation of a spacecraft using an assortment of modules that comply with the standard. The standard preferably includes both mechanical and electrical compatibility criteria. To assure physical/mechanical compatibility, the structure of each module is constrained to be compatible with any other compatible module. To minimize the interference among modules, the extent of each module in select dimensions is also constrained. To assure functional compatibility, a common communication format is used to interface with each module, and each public-function module is configured to respond to requests for function capabilities that it can provide to other functions. Each module is preferably designed to provide structural support to the assemblage of modules, and an anchor module is provided or defined for supporting the entire assemblage and coupling the assemblage to other structures, such as a launch vehicle.

摘要翻译： 航天器结构和伴随标准允许使用符合标准的各种模块来创建航天器。 该标准优选地包括机械和电气兼容性标准。 为了确保物理/机械兼容性，每个模块的结构被限制为与任何其他兼容模块兼容。 为了最小化模块之间的干扰，选择尺寸中的每个模块的范围也受到限制。 为了确保功能兼容性，使用通用通信格式与每个模块进行接口，并且每个公共功能模块被配置为响应其可以提供给其他功能的功能能力的请求。 每个模块优选地设计成为模块的组合提供结构支撑，并且提供或限定锚模块以支撑整个组件并将组合件联接到诸如运载火箭的其他结构。

公开(公告)号：US20070081379A1

公开(公告)日：2007-04-12

申请号：US11234346

申请日：2005-09-23

申请人： Michael Clinton ,  Stephen Heinrich-Barna ,  Theodore Houston ,  George Jamison ,  Kun-hsi Li ,  Jonathon Miller ,  Bryan Sheffield

发明人： Michael Clinton ,  Stephen Heinrich-Barna ,  Theodore Houston ,  George Jamison ,  Kun-hsi Li ,  Jonathon Miller ,  Bryan Sheffield

IPC分类号： G11C11/24

CPC分类号： G11C11/419

摘要： One embodiment provides a system to assist setting a state of a latch system. The system includes a latch system connected to a node, the latch system residing in one of a first state and a second state. A charge storage device is coupled to maintain the node at a first voltage according to an amount of stored charge. A write assist system is connected between the node and a second voltage. The write assist network is configured, when the node is selected, to discharge the charge storage device and to pull the node from the first voltage to a discharge voltage that is outside a range defined by the first voltage and the second voltage to facilitate setting the latch system to another of the first state and the second state.

摘要翻译： 一个实施例提供一种帮助设置闩锁系统的状态的系统。 系统包括连接到节点的锁存系统，锁存系统驻留在第一状态和第二状态之一中。 电荷存储装置被耦合以根据存储的电荷的量将节点维持在第一电压。 写入辅助系统连接在节点和第二电压之间。 写入辅助网络被配置为当选择节点时，放电电荷存储装置并且将节点从第一电压拉到超出由第一电压和第二电压限定的范围的放电电压，以便于设置 将系统锁定到第一状态和第二状态中的另一状态。

公开(公告)号：US07191984B2

公开(公告)日：2007-03-20

申请号：US11151908

申请日：2005-06-14

申请人： Mark Carl Barton ,  Jonathon Miller

发明人： Mark Carl Barton ,  Jonathon Miller

IPC分类号： B64G1/58

CPC分类号： B64G1/506

摘要： A thermal management system for a spacecraft module includes a baseplate and wall system that is precharacterized to provide a given level of thermal performance regardless of an orientation of the spacecraft relative to a source of solar energy. The system is characterized at a worst-case hot orientation, and at a worst-case cold orientation. The characterization provides a maximum temperature and a minimum temperature of components mounted on the baseplate as a function of the height of the walls. The height of the walls is selected to provide a suitable temperature range for the components, based on the power dissipation of the components. The system is designed to be symmetric, so that this temperature range is assured regardless of the orientation of the spacecraft.

摘要翻译： 用于航天器模块的热管理系统包括基板和壁系统，该基板和壁系统具有预特性以提供给定水平的热性能，而不管航天器相对于太阳能源的取向如何。 该系统的特征在于最坏情况下的热定向，并且处于最坏情况下的冷定向。 表征提供了作为墙壁高度的函数的安装在基板上的部件的最高温度和最小温度。 基于部件的功率耗散，选择壁的高度以为部件提供合适的温度范围。 该系统被设计为对称的，使得无论航天器的方向如何，该温度范围都是有保证的。

公开(公告)号：US20060016935A1

公开(公告)日：2006-01-26

申请号：US11151906

申请日：2005-06-14

申请人： Luis Jordan ,  Thomas Vanek ,  Scott McDermott ,  Jonathon Miller ,  Simon Weiss ,  Robert Summers

发明人： Luis Jordan ,  Thomas Vanek ,  Scott McDermott ,  Jonathon Miller ,  Simon Weiss ,  Robert Summers

IPC分类号： B64G1/00

CPC分类号： B64G1/10 ,  B64G1/428 ,  B64G2001/1092

摘要： A spacecraft architecture and accompanying standard allows for the creation of a spacecraft using an assortment of modules that comply with the standard. The standard preferably includes both mechanical and electrical compatibility criteria. To assure physical/mechanical compatibility, the structure of each module is constrained to be compatible with any other compatible module. To minimize the interference among modules, the extent of each module in select dimensions is also constrained. To assure functional compatibility, a common communication format is used to interface with each module, and each public-function module is configured to respond to requests for function capabilities that it can provide to other functions. Each module is preferably designed to provide structural support to the assemblage of modules, and an anchor module is provided or defined for supporting the entire assemblage and coupling the assemblage to other structures, such as a launch vehicle.

摘要翻译： 航天器结构和伴随标准允许使用符合标准的各种模块来创建航天器。 该标准优选地包括机械和电气兼容性标准。 为了确保物理/机械兼容性，每个模块的结构被限制为与任何其他兼容模块兼容。 为了最小化模块之间的干扰，选择尺寸中的每个模块的范围也受到限制。 为了确保功能兼容性，使用通用通信格式与每个模块进行接口，并且每个公共功能模块被配置为响应其可以提供给其他功能的功能能力的请求。 每个模块优选地设计成为模块的组合提供结构支撑，并且提供或限定锚模块以支撑整个组件并将组合件联接到诸如运载火箭的其他结构。