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1. 发明申请

US20070063106A1 Thermal Deformation Determination For Payload Pointing Using Space-Based Beacon 有权
标题翻译：使用基于空间的信标进行有效载荷指向的热变形确定
公开(公告)号：US20070063106A1
公开(公告)日：2007-03-22
申请号：US11533165
申请日：2006-09-19
申请人： Leonard Plotke , Ketao Liu
发明人： Leonard Plotke , Ketao Liu
IPC分类号： B64G1/52
CPC分类号： B64G1/24 , B64G1/36
摘要： A system and associated method for compensating for thermal deformation of a spaced-based structure having a spacecraft payload. The system including a beacon source coupled to a first spacecraft for transmitting a first signal and a beacon sensor coupled to a second spacecraft for receiving the first signal and providing measurement data derived from the first signal. At least one attitude sensing device is coupled to the second spacecraft for determining estimated spacecraft attitude data for the second spacecraft. A processor on the second spacecraft is configured to process ephemeris data of the first and second spacecraft, beacon measurement data, estimated spacecraft attitude data, and gimbal angular position data to estimate spacecraft structural deformation.
摘要翻译：一种用于补偿具有航天器有效载荷的基于间隔的结构的热变形的系统和相关方法。该系统包括耦合到第一航天器的用于发射第一信号的信标源和耦合到第二航天器的信标传感器，用于接收第一信号并提供从第一信号导出的测量数据。至少一个姿态感测装置耦合到第二航天器，用于确定第二航天器的估计的航天器姿态数据。第二航天器上的处理器被配置为处理第一和第二航天器的星历数据，信标测量数据，估计的航天器姿态数据和万向角位置数据以估计航天器结构变形。

2. 发明申请

US20060054745A1 Thermal deformation determination for payload pointing using space-based beacon 有权
标题翻译：使用基于空间的信标的有效载荷指向的热变形确定
公开(公告)号：US20060054745A1
公开(公告)日：2006-03-16
申请号：US10929844
申请日：2004-08-30
申请人： Leonard Plotke , Ketao Liu
发明人： Leonard Plotke , Ketao Liu
IPC分类号： B64G1/36
CPC分类号： B64G1/24 , B64G1/36
摘要： A system and associated method for compensating for thermal deformation of a spaced-based structure having a spacecraft payload. The system including a beacon source coupled to a first spacecraft for transmitting a first signal and a beacon sensor coupled to a second spacecraft for receiving the first signal and providing measurement data derived from the first signal. At least one attitude sensing device is coupled to the second spacecraft for determining estimated spacecraft attitude data for the second spacecraft. A processor on the second spacecraft is configured to process ephemeris data of the first and second spacecraft, beacon measurement data, estimated spacecraft attitude data, and gimbal angular position data to estimate spacecraft structural deformation.
摘要翻译：一种用于补偿具有航天器有效载荷的基于间隔的结构的热变形的系统和相关方法。该系统包括耦合到第一航天器的用于发射第一信号的信标源和耦合到第二航天器的信标传感器，用于接收第一信号并提供从第一信号导出的测量数据。至少一个姿态感测装置耦合到第二航天器，用于确定第二航天器的估计的航天器姿态数据。第二航天器上的处理器被配置为处理第一和第二航天器的星历数据，信标测量数据，估计的航天器姿态数据和万向角位置数据以估计航天器结构变形。

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