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1. 发明授权

US08868263B2 Spacecraft momentum management using solar array 有权
标题翻译：航天器动力管理采用太阳能阵列
公开(公告)号：US08868263B2
公开(公告)日：2014-10-21
申请号：US13115370
申请日：2011-05-25
申请人： Mohammad Saghir Munir , John Hutton Cooper , Philip Conway Hirschberg
发明人： Mohammad Saghir Munir , John Hutton Cooper , Philip Conway Hirschberg
IPC分类号： B64G1/24 , G05D1/00 , G05D1/08
CPC分类号： G05D1/0883 , B64G1/24 , B64G1/26 , B64G1/283 , B64G1/361 , B64G1/365 , B64G1/405 , B64G1/407 , B64G1/44
摘要： Stored momentum on a spacecraft is managed by determining a target profile of stored momentum as a function of time for the spacecraft; measuring a difference between a momentum value actually stored on the spacecraft and a desired momentum value, where the desired momentum value substantially conforms to the target profile at a particular time; reducing the difference by producing a torque on the spacecraft, where the torque results from selectively controlling at least one solar array position offset angle, the offset angle being an offset of at least one solar array of the spacecraft from a nominal sun pointing direction.
摘要翻译：通过确定作为航天器时间的函数的存储动量的目标轮廓来管理航天器上的存储动量; 测量实际存储在航天器上的动量值与期望动量值之间的差异，其中期望动量值在特定时间基本上符合目标轮廓; 通过在航天器上产生扭矩来减小差异，其中扭矩由选择性地控制至少一个太阳能阵列位置偏移角度而产生，该偏移角度是航天器的至少一个太阳能阵列与标称太阳指向方向的偏移。

2. 发明申请

US20120303185A1 SPACECRAFT MOMENTUM MANAGEMENT USING SOLAR ARRAY 有权
标题翻译：使用太阳辐射阵列的空间管理
公开(公告)号：US20120303185A1
公开(公告)日：2012-11-29
申请号：US13115370
申请日：2011-05-25
申请人： Mohammad Saghir Munir , John Hutton Cooper , Philip Conway Hirschberg
发明人： Mohammad Saghir Munir , John Hutton Cooper , Philip Conway Hirschberg
IPC分类号： B64G1/24 , G05D1/00
CPC分类号： G05D1/0883 , B64G1/24 , B64G1/26 , B64G1/283 , B64G1/361 , B64G1/365 , B64G1/405 , B64G1/407 , B64G1/44
摘要： Stored momentum on a spacecraft is managed by determining a target profile of stored momentum as a function of time for the spacecraft; measuring a difference between a momentum value actually stored on the spacecraft and a desired momentum value, where the desired momentum value substantially conforms to the target profile at a particular time; reducing the difference by producing a torque on the spacecraft, where the torque results from selectively controlling at least one solar array position offset angle, the offset angle being an offset of at least one solar array of the spacecraft from a nominal sun pointing direction.
摘要翻译：通过确定作为航天器时间的函数的存储动量的目标轮廓来管理航天器上的存储动量; 测量实际存储在航天器上的动量值与期望动量值之间的差异，其中期望动量值在特定时间基本上符合目标轮廓; 通过在航天器上产生扭矩来减小差异，其中扭矩由选择性地控制至少一个太阳能阵列位置偏移角度而产生，该偏移角度是航天器的至少一个太阳能阵列与标称太阳指向方向的偏移。

3. 发明申请

US20120097797A1 SPACECRAFT MOMENTUM MANAGEMENT 有权
标题翻译： SPACECRAFT MOMENTUM管理
公开(公告)号：US20120097797A1
公开(公告)日：2012-04-26
申请号：US13326654
申请日：2011-12-15
申请人： Byoungsam Woo , Mohammad Saghir Munir , Kam K. Chan
发明人： Byoungsam Woo , Mohammad Saghir Munir , Kam K. Chan
IPC分类号： B64G1/10 , G05D1/00 , B64G1/24
CPC分类号： B64G1/26 , B64G1/242 , F03H1/0037
摘要： Three-axis spacecraft momentum management is performed for a spacecraft traveling along a trajectory, by an actuator including at least one thruster disposed on a single positioning mechanism. As the spacecraft travels along the trajectory, a desired line of thrust undergoes a substantial rotation in inertial space. When the spacecraft is located at a first location on the trajectory, the single positioning mechanism orients the thruster so as to produce a first torque to manage stored momentum in at least one of a first and a second of the three inertial spacecraft axes. When the spacecraft is located at a second location on the trajectory, the single positioning mechanism orients the thruster so as to produce a second torque to manage stored momentum in at least a third of the three inertial spacecraft axes.
摘要翻译：通过包括设置在单个定位机构上的至少一个推进器的致动器执行沿着轨迹行进的航天器的三轴航天器动量管理。当航天器沿着轨迹行进时，所需的推力线在惯性空间中经历相当大的旋转。当航天器位于轨迹上的第一位置时，单个定位机构使推进器定向以产生第一扭矩以管理三个惯性航天器轴中的第一和第二个中的至少一个中的存储动量。当航天器位于轨迹上的第二位置时，单个定位机构使推进器定向以产生第二扭矩以管理三个惯性航天器轴线中至少三分之一的存储动量。

4. 发明申请

US20140278209A1 Method for Tracking Defects on a Photomask Across Repeated Inspections 审中-公开
标题翻译：在重复检查中跟踪光掩模缺陷的方法
公开(公告)号：US20140278209A1
公开(公告)日：2014-09-18
申请号：US13798104
申请日：2013-03-13
申请人： Mohammad Saghir Munir
发明人： Mohammad Saghir Munir
IPC分类号： G01B21/16
CPC分类号： G01B21/20 , G01B11/24 , G01N21/9501 , G03F1/84
摘要： This invention allows tracking of a defect across multiple inspections. The inventive solution translates every inspection record into a common set of fields that are first archived into a relational database. Then the defect coordinates from the inspection records of the same mask are all transformed into a common reference frame having the same origin and orientation with respect to the mask coordinate system. Following this, the defect having coordinates within a given tolerance distance are paired up and reported to the user.
摘要翻译：本发明允许在多次检查之间追踪缺陷。本发明的解决方案将每个检查记录转换成首先归档到关系数据库中的一组公共字段。然后，来自相同掩模的检查记录的缺陷坐标都被转换成相对于掩模坐标系具有相同原点和取向的公共参考帧。此后，具有给定公差距离内的坐标的缺陷被配对并向用户报告。

5. 发明授权

US09557169B2 Method for tracking defects on a photomask across repeated inspections 有权
标题翻译：通过重复检查跟踪光掩模上的缺陷的方法
公开(公告)号：US09557169B2
公开(公告)日：2017-01-31
申请号：US13798104
申请日：2013-03-13
申请人： Mohammad Saghir Munir
发明人： Mohammad Saghir Munir
IPC分类号： G01C9/00 , G01B21/20 , G01B11/24 , G01N21/95 , G03F1/84
CPC分类号： G01B21/20 , G01B11/24 , G01N21/9501 , G03F1/84
摘要： This invention allows tracking of a defect across multiple inspections. The inventive solution translates every inspection record into a common set of fields that are first archived into a relational database. Then the defect coordinates from the inspection records of the same mask are all transformed into a common reference frame having the same origin and orientation with respect to the mask coordinate system. Following this, the defect having coordinates within a given tolerance distance are paired up and reported to the user.
摘要翻译：本发明允许在多次检查之间追踪缺陷。本发明的解决方案将每个检查记录转换成首先归档到关系数据库中的一组公共字段。然后，来自相同掩模的检查记录的缺陷坐标都被转换成相对于掩模坐标系具有相同原点和取向的公共参考帧。此后，具有给定公差距离内的坐标的缺陷被配对并向用户报告。

6. 发明授权

US09108749B2 Spacecraft momentum management 有权
标题翻译：航天器动量管理
公开(公告)号：US09108749B2
公开(公告)日：2015-08-18
申请号：US13326654
申请日：2011-12-15
申请人： Byoungsam Woo , Mohammad Saghir Munir , Kam K. Chan
发明人： Byoungsam Woo , Mohammad Saghir Munir , Kam K. Chan
IPC分类号： B64G1/26 , B64G1/24 , F03H1/00
CPC分类号： B64G1/26 , B64G1/242 , F03H1/0037
摘要： Three-axis spacecraft momentum management is performed for a spacecraft traveling along a trajectory, by an actuator including at least one thruster disposed on a single positioning mechanism. As the spacecraft travels along the trajectory, a desired line of thrust undergoes a substantial rotation in inertial space. When the spacecraft is located at a first location on the trajectory, the single positioning mechanism orients the thruster so as to produce a first torque to manage stored momentum in at least one of a first and a second of the three inertial spacecraft axes. When the spacecraft is located at a second location on the trajectory, the single positioning mechanism orients the thruster so as to produce a second torque to manage stored momentum in at least a third of the three inertial spacecraft axes.
摘要翻译：通过包括设置在单个定位机构上的至少一个推进器的致动器执行沿着轨迹行进的航天器的三轴航天器动量管理。当航天器沿着轨迹行进时，所需的推力线在惯性空间中经历相当大的旋转。当航天器位于轨迹上的第一位置时，单个定位机构使推进器定向以产生第一扭矩以管理三个惯性航天器轴中的第一和第二个中的至少一个中的存储动量。当航天器位于轨迹上的第二位置时，单个定位机构使推进器定向以产生第二扭矩以管理三个惯性航天器轴线中至少三分之一的存储动量。

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