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1. 发明授权

US6019320A Spacecraft acquisition of sun pointing 失效
标题翻译：航天器收购太阳指向
公开(公告)号：US6019320A
公开(公告)日：2000-02-01
申请号：US153123
申请日：1998-09-15
申请人： Piyush R. Shah , Douglas J. Bender
发明人： Piyush R. Shah , Douglas J. Bender
IPC分类号： B64G1/24 , B64G1/28 , B64G1/36 , G05D1/08
CPC分类号： G05D1/0883 , B64G1/24 , B64G1/283 , B64G1/288 , B64G1/36 , B64G1/363 , B64G1/365 , B64G1/285 , B64G2001/245
摘要： A system and method for acquiring Sun pointing in a three-axis stabilized spacecraft including slewing at least one solar wing until the Sun is detected, determining an initial Sun vector, performing one or more rotations of the spacecraft body so as to bring the instantaneous Sun vector coincident with a preferred final Sun vector, at least one rotation about an optimal axis, and slewing at least one solar wing to a preferred attitude relative to the Sun. In one embodiment, the optimal axis is chosen so as to minimize the time required to achieve an optimal thermal attitude. In another embodiment, the optimal axis is chosen so as to minimize the time required to align the instantaneous Sun vector with the final desired Sun vector. In a further embodiment, the optimal axis is chosen so as to maintain Earth lock.
摘要翻译：一种用于获取Sun指向三轴稳定的航天器的系统和方法，包括至少一个太阳翼的回转，直到检测到太阳，确定初始的太阳矢量，执行航天器主体的一个或多个旋转，以使瞬时的太阳与优选的最后的Sun矢量重合的矢量，围绕最佳轴线至少一个旋转，并且将至少一个太阳翼旋转到相对于太阳的优选姿态。在一个实施例中，选择最佳轴线以便最小化实现最佳热姿态所需的时间。在另一个实施例中，选择最佳轴使得将瞬时的Sun矢量与最终期望的Sun矢量对准所需的时间最小化。在另一个实施例中，选择最佳轴线以便保持接地锁定。

2. 发明授权

US06076774A Fuel and thermal optimal spiral earth acquisition 有权
标题翻译：燃料和热优化螺旋接地采集
公开(公告)号：US06076774A
公开(公告)日：2000-06-20
申请号：US132343
申请日：1998-08-12
申请人： Piyush R. Shah , Thomas M. Tanner , Richard A. Noyola
发明人： Piyush R. Shah , Thomas M. Tanner , Richard A. Noyola
IPC分类号： B64G1/24 , B64G1/26 , B64G1/28 , B64G1/36
CPC分类号： B64G1/24 , B64G1/285 , B64G1/363 , B64G1/365 , B64G1/26 , B64G2001/245
摘要： A system and method for acquiring the Earth by a three-axis stabilized spacecraft in the presence of a significantly time-varying Sun-Earth angle including obtaining an Earth cone described by rotating the nadir vector about the Sun vector, slewing the spacecraft about an axis until the Earth sensor boresight touches an edge of the Earth cone, updating the Earth cone due to the changing Sun-Earth separation angle, performing a spiral coning maneuver about the updated Earth cone until the Earth sensor detects the Earth, and locking onto the Earth so as to hold the Earth sensor boresight coincident with the nadir vector. Additionally, the spacecraft may be rotated about the nadir vector so as to bring the spacecraft into a desired final attitude.
摘要翻译：一种用于在存在显着时变的太阳地角的情况下通过三轴稳定的航天器获取地球的系统和方法，包括通过围绕太阳矢量旋转最低底矢量来获得描述的地球锥体，使航天器围绕轴旋转直到地球传感器视轴接触到地球锥体的边缘，由于太阳 - 地球分离角度的变化更新了地球锥体，对更新的地球锥体进行螺旋锥形操纵，直到地球传感器检测到地球并锁定在地球上以便将地球传感器的视轴与最低底矢量保持一致。此外，航天器可以围绕天底矢量旋转，以使飞船进入期望的最终姿态。

3. 发明授权

US06282467B1 Three-axis inertial attitude determination for spinning spacecraft 失效
标题翻译：旋转航天器的三轴惯性姿态测定
公开(公告)号：US06282467B1
公开(公告)日：2001-08-28
申请号：US08949634
申请日：1997-10-14
申请人： Piyush R. Shah , Garry Didinsky , David S. Uetrecht
发明人： Piyush R. Shah , Garry Didinsky , David S. Uetrecht
IPC分类号： B64G124
CPC分类号： B64G1/363 , B64G1/28 , B64G1/281 , B64G1/288 , B64G1/36 , B64G1/365 , B64G3/00
摘要： A system and method for determining the attitude in an inertial frame of a spacecraft spinning about an axis in a body frame including determining momentum vector direction in the inertial frame; determining momentum vector direction in the body frame; acquiring information from an at least single-axis sensor; obtaining reference information on the at least single-axis sensor; updating the attitude in the inertial reference frame using the momentum vector direction in the inertial frame, the momentum vector direction in the body frame, the output of the at least single-axis sensor, and the reference information on the at least single-axis sensor; and propagating the attitude using data from one or more inertial sensors.
摘要翻译：一种用于确定在包括确定惯性框架中的动量矢量方向的人体框架中围绕轴线旋转的航天器的惯性框架中的姿态的系统和方法; 确定身体框架中的动量矢量方向; 从至少单轴传感器获取信息; 获得所述至少单轴传感器的参考信息; 使用惯性框架中的动量矢量方向，身体框架中的动量向量方向，至少单轴传感器的输出以及至少单轴传感器的参考信息来更新惯性参考系中的姿态 ; 并且使用来自一个或多个惯性传感器的数据来传播姿态。

4. 发明授权

US6003818A System and method for utilizing stored momentum to optimize spacecraft slews 失效
标题翻译：利用存储的动量来优化航天器的扭矩的系统和方法
公开(公告)号：US6003818A
公开(公告)日：1999-12-21
申请号：US38022
申请日：1998-03-11
申请人： Piyush R. Shah , Douglas J. Bender , David S. Uetrecht
发明人： Piyush R. Shah , Douglas J. Bender , David S. Uetrecht
IPC分类号： B64G1/28 , B64G1/36 , G05D1/08
CPC分类号： G05D1/0883 , B64G1/283 , B64G1/288 , B64G1/36 , B64G1/363 , B64G1/365 , B64G2001/245
摘要： A system and method for slewing a spacecraft with a reaction wheel system including determining initial total momentum, determining maximum forward and reverse rates that can be realized within the reaction wheel system maximum storage capacity, determining a slew rate and slew direction from the maximum forward and reverse rates so as to minimize slew time for known slew angles or maximize slew rate for arbitrary slew angles, and slewing the spacecraft.
摘要翻译：一种利用反作用轮系统回转航天器的系统和方法，包括确定初始总动量，确定可在反馈轮系统最大存储容量内实现的最大正向和反向速率，从最大前进确定转换速率和转动方向，以及反转速率，以便使已知的转换角度的转换时间最小化，或者最大化任意摆动角度的转换速率，以及旋转航天器。

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