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1. 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。

2. 发明授权

US6053455A Spacecraft attitude control system using low thrust thrusters 失效
标题翻译：航天器姿态控制系统采用低推力推力器
公开(公告)号：US6053455A
公开(公告)日：2000-04-25
申请号：US10718
申请日：1998-01-22
申请人： Xen Price , Thomas Randolph , Kam K. Chan , Ahmed Kamel
发明人： Xen Price , Thomas Randolph , Kam K. Chan , Ahmed Kamel
IPC分类号： B64G1/26 , B64G1/28 , B64G1/36
CPC分类号： B64G1/26 , B64G1/28 , B64G1/36 , B64G2001/247
摘要： A spacecraft, such as a geosynchronous weather or communications satellite, is constructed to include a plurality of low thrust thrusters mounted at predetermined locations on at least one of a spacecraft appendage or a spacecraft bus. The plurality of low thrust thrusters are fired in pairs for at least one of removing a disturbance torque or providing fine pointing attitude control. In one embodiment the low thrust thrusters are mounted on a solar array panel, thereby increasing the moment arm and enhancing the thrust output of the low thrust thrusters. In one embodiment a spacecraft has a plurality of low thrust thrusters arranged as at least two sets of two low thrust thrusters, individual ones of the low thrust thrusters of a set being disposed in a V-configuration and mounted at predetermined locations on at least one of a spacecraft appendage or a spacecraft bus. The plurality of low thrust thrusters are selectively fired for achieving control of 3-axes of spacecraft attitude or momentum.
摘要翻译：诸如地球同步天气或通信卫星的航天器被构造成包括安装在航天器附件或航天器总线中的至少一个上的预定位置处的多个低推力推进器。多个低推力推进器被成对地烧制以去除干扰转矩或提供精细指向姿态控制中的至少一个。在一个实施例中，低推力推进器安装在太阳能阵列面板上，从而增加了力矩臂并增强了低推力推进器的推力输出。在一个实施例中，航天器具有多个低推力推进器，其布置为至少两组两个低推力推进器，其中一组低推力推进器中的各个被推置成V形并且安装在至少一个的航天器附件或航天器总线。选择性地发射多个低推力推进器以实现对航天器姿态或动量的三轴的控制。

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. 发明授权

US5957411A Method using double thruster firings to deadbeat flexible solar array structural oscillations 失效
标题翻译：使用双推进器启动的方法来使柔性太阳能阵列结构振荡
公开(公告)号：US5957411A
公开(公告)日：1999-09-28
申请号：US998173
申请日：1997-12-24
申请人： Tung Y Liu , Kam K Chan
发明人： Tung Y Liu , Kam K Chan
IPC分类号： B64G1/26 , B64G1/44 , G05D1/08
CPC分类号： G05D1/0883 , B64G1/26 , B64G2001/245
摘要： A spacecraft includes a plurality of thrusters mounted at predetermined locations on a spacecraft structure, individual ones the plurality of thrusters being fired for generating a torque about a desired axis. The firing of a thruster is partitioned into two firings that are offset in time by an amount .DELTA.t, wherein .DELTA.t=(1/2).times.(1/F).times.SF, where F is a dominant modal frequency, in Hertz, for any particular axis (nominally the 1st mode) of the spacecraft structure, and where SF is a scale factor that is adjustable about the frequency. In a presently preferred embodiment the thruster is a low thrust thruster that is mounted on a solar array panel, and the thrusters are fired in pairs.
摘要翻译：航天器包括安装在航天器结构上的预定位置处的多个推进器，单个的推进器被点燃以产生围绕期望轴线的转矩。推进器的点火被分成两次，其时间偏移量DELTA t，其中DELTA t =（+ E，fra 1/2 + EE）x（1 / F）xSF，其中F是主要模态频率，以赫兹为单位，用于航天器结构的任何特定轴（名义上为第一模式），以及其中SF是关于频率可调整的比例因子。在目前优选的实施例中，推进器是安装在太阳能阵列面板上的低推力推进器，并且推进器成对地发射。

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