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1. 发明授权

US5540405A Method and apparatus for compensating for magnetic disturbance torques on a satellite 失效
标题翻译：用于补偿卫星上的磁扰动转矩的方法和装置
公开(公告)号：US5540405A
公开(公告)日：1996-07-30
申请号：US89381
申请日：1993-07-09
申请人： Douglas J. Bender , William F. Hummel
发明人： Douglas J. Bender , William F. Hummel
IPC分类号： B64G1/24 , B64G1/28 , B64G1/32 , B64G1/34 , B64G1/36 , G05D1/08
CPC分类号： G05D1/0883 , B64G1/24 , B64G1/32 , B64G1/34 , B64G1/366 , B64G1/285 , B64G1/288 , B64G1/361 , B64G1/363 , B64G1/365
摘要： This invention discloses a method for compensating for the disturbance torque on an orbiting satellite (10) from the interference of the earth's magnetic field lines with particular current loops associated with the satellite (10). The current flow in these current loops on the satellite (10) is measured by a current sensing device (42). A scaling factor (44,46) is applied to the measured currents to derive an estimated disturbance torque in particular axes of the satellite's attitude. The estimated magnetic disturbance torques are applied, along with other control torques, to a satellite actuation device (38). The actuation device (38) actuates the satellite (10) in the particular axes to compensate for the disturbance torques being applied to the satellite (10).
摘要翻译：本发明公开了一种用于补偿轨道卫星（10）上的干扰转矩与地球磁场线与卫星（10）相关联的特定电流环路的干扰的方法。在卫星（10）上的这些电流回路中的电流通过电流检测装置（42）测量。对测量的电流施加比例因子（44,46）以导出卫星姿态的特定轴的估计扰动转矩。估计的磁干扰转矩与其他控制转矩一起施加到卫星致动装置（38）。致动装置（38）在特定轴线上致动卫星（10），以补偿施加于卫星（10）的干扰转矩。

2. 发明申请

US20080135686A1 METHOD AND SYSTEM FOR SPACECRAFT POWER ACQUISITION USING SINGLE-AXIS SLIT SUN SENSOR 有权
标题翻译：使用单轴SLIT SUN传感器进行功率采集的方法和系统
公开(公告)号：US20080135686A1
公开(公告)日：2008-06-12
申请号：US11608140
申请日：2006-12-07
申请人： Hanching Grant Wang , Sadek W. Mansour , Douglas J. Bender
发明人： Hanching Grant Wang , Sadek W. Mansour , Douglas J. Bender
IPC分类号： B64G1/36
CPC分类号： B64G1/363 , B64G1/44 , G01S3/7862
摘要： A method for spacecraft power acquisition is provided using single-axis slit sun sensors for both wing-stowed and wing-deployed spacecraft configurations. The method for wing-deployed spacecraft includes initializing a solar wing of the spacecraft to search for sun; rotating the spacecraft about a search axis substantially parallel to a slit sun sensor field of view; monitoring the slit sun sensor for a time of arrival signal; and wherein, if the time of arrival signal occurs, the spacecraft is rotated along the search axis to an orientation where the time of arrival signal occurred and the spacecraft is placed in stable rotation about an axis substantially parallel to a solar wing longitudinal axis; and for a non-occurrence of the time of arrival signal, the spacecraft is slewed about a keyhole axis substantially perpendicular to the search axis to move the sun away from a keyhole.
摘要翻译：使用单轴狭缝太阳传感器提供飞行器功率采集的方法，用于机翼收起和机翼部署的航天器配置。机翼部署的航天器的方法包括初始化太空飞船的太阳能翼，以搜寻太阳; 围绕基本上平行于狭缝太阳传感器视场的搜索轴旋转航天器; 监测狭缝太阳传感器的到达时间信号; 并且其中，如果到达时间信号发生，则航天器沿着搜索轴旋转到出现时间到达信号的方向，并且航天器围绕基本上平行于太阳翼纵向轴线的轴线被稳定地旋转; 并且为了不发生到达时间信号，航天器围绕基本上垂直于搜索轴线的键孔轴旋转，以将太阳从锁孔移开。

3. 发明授权

US5337981A Method and apparatus for compensating for solar torque transients on a satellite during a solar eclipse 失效
标题翻译：在日食期间补偿卫星上太阳能转矩瞬变的方法和装置
公开(公告)号：US5337981A
公开(公告)日：1994-08-16
申请号：US800775
申请日：1991-11-27
申请人： Douglas J. Bender
发明人： Douglas J. Bender
IPC分类号： B64G1/24 , B64G1/36 , G05D1/08
CPC分类号： G05D1/0883 , B64G1/24 , B64G1/36
摘要： This invention discloses a method for determining when an orbiting satellite (10) is eclipsed from the sun in order to remove control torques to the satellite (10) which compensate for the disturbance of solar pressure on the satellite (10). A current measuring device (46) measures the current traveling through a particular circuit associated with the satellite (10) which is indicative of the satellite batteries being discharged, as would occur during an eclipse. The measured current is applied to a threshold logic circuit (48) which sends a signal to a control compensator (36) if the measured current exceeds a predetermined threshold level. Consequently, the compensation provided by the control compensator (36) removes the compensation for compensating for solar pressure when the satellite (10) is in an eclipse. In a second implementation, the threshold logic circuit (48) is replaced with a proportionality logic circuit to compensate for the effects of partial eclipses.
摘要翻译：本发明公开了一种确定轨道卫星何时从太阳中掉下来的方法，以便去除对卫星（10）的控制力矩，以补偿卫星（10）上太阳能压力的干扰。电流测量装置（46）测量在与食物相关联的特定电路（10）的电流，其指示卫星电池被排出，如在日食期间将发生的那样。测量的电流被施加到门限逻辑电路（48），如果所测量的电流超过预定的阈值电平，则逻辑电路向控制补偿器（36）发送信号。因此，控制补偿器（36）提供的补偿消除了当卫星（10）处于日食时补偿太阳能压力的补偿。在第二实施例中，阈值逻辑电路（48）被替换为比例逻辑电路以补偿部分日食的影响。

4. 发明授权

US5257759A Method and apparatus for controlling a solar wing of a satellite using a sun sensor 失效
标题翻译：使用太阳传感器控制卫星的太阳能翼的方法和装置
公开(公告)号：US5257759A
公开(公告)日：1993-11-02
申请号：US800892
申请日：1991-11-27
申请人： Douglas J. Bender
发明人： Douglas J. Bender
IPC分类号： B64G1/24 , B64G1/28 , B64G1/36 , B64G1/44 , G01S3/786
CPC分类号： B64G1/44 , B64G1/363 , G01S3/7862 , B64G1/285 , B64G1/365
摘要： This invention discloses a method for maintaining a desirable orientation of the solar wings of an orbiting satellite (10) relative to the sun. A dual array of sun sensors (26,28) is positioned on a body (12) of the satellite (10) in order to get a measurement of the position of the sun relative to the body (12) once per every orbit of the satellite (10). In addition, an estimate of the position of the solar wings (16,17) relative to the body (12) of the satellite (10) is attained. The sun-to-body angle is then subtracted from the body-to-wing angle to drive an error signal which is applied to a wing driver mechanism in order to maintain the solar wings (16,17) of the satellite (10) in a proper orientation relative to the sun.

5. 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。

6. 发明授权

US5557285A Gimbal control system 失效
标题翻译：云台控制系统
公开(公告)号：US5557285A
公开(公告)日：1996-09-17
申请号：US185346
申请日：1994-01-24
申请人： Douglas J. Bender , Stuart F. Bockman , Bruce N. Eyerly , John J. Anagnost
发明人： Douglas J. Bender , Stuart F. Bockman , Bruce N. Eyerly , John J. Anagnost
IPC分类号： H01Q3/08 , B64G1/22 , B64G1/24 , B64G1/28 , B64G1/36 , G01S3/42 , H01Q1/18 , H01Q1/28 , H01Q3/00
CPC分类号： H01Q1/18 , B64G1/22 , B64G1/24 , B64G1/288 , B64G1/36
摘要： A multi-loop control system for a gimballed antenna that employs devices for measuring both absolute line-of-sight (an autotrack receiver or beacon tracker) and relative angular position (a resolver). The control system uses both signals simultaneously, thereby increasing the performance and pointing accuracy capability. Two control loops operate simultaneously to provide for optimum performance. The first loop is an inner high-bandwidth control loop that uses the relative gimbal angle measurement to control pointing of the antenna along a precommanded profile. The inner loop may run alone to provide for coarse pointing. When available, the line-of sight measurement is used in a low-bandwidth outer loop to provide corrections to the command profile of the inner loop. Control logic is provided that allows switching between several control modes. By using the present invention, antenna tracking control performance is maximized, especially in the presence of attitude disturbances of a spacecraft or significant flexible interactions.
摘要翻译：用于测量绝对视线（自动跟踪接收机或信标跟踪器）和相对角位置（分解器）的设备的万向天线的多回路控制系统。控制系统同时使用两个信号，从而提高性能和指点精度。两个控制回路同时工作以提供最佳性能。第一个环路是一个内部高带宽控制环路，它利用相对的万向角测量来控制天线沿着预先命令的轮廓的指向。内循环可以单独运行以提供粗略指向。当可用时，视距测量用于低带宽外部环路，以对内部循环的命令曲线进行校正。提供了允许在几种控制模式之间切换的控制逻辑。通过使用本发明，天线跟踪控制性能最大化，特别是在存在航天器的姿态干扰或显着灵活的相互作用的情况下。

7. 发明授权

US4752884A Precision platform pointing controller for a dual-spin spacecraft 失效
标题翻译：双旋转飞行器的精准平台指向控制器
公开(公告)号：US4752884A
公开(公告)日：1988-06-21
申请号：US756867
申请日：1985-07-18
申请人： Loren I. Slafer , Douglas J. Bender , John F. Yocum
发明人： Loren I. Slafer , Douglas J. Bender , John F. Yocum
IPC分类号： B64G1/24 , B64G1/28 , B64G1/36 , G01C21/24 , G05D1/08
CPC分类号： B64G1/36 , B64G1/24 , B64G1/281 , G05D1/0883
摘要： A pointing apparatus for a dual-spin spacecraft utilizing a first sensor for sensing the time of arrival of an inertial attitude reference as the spinning portion of the spacecraft rotates, and a second sensor for sensing the time of arrival of an index reference which relates the position of the despun portion with the spinning portion. A digital processor estimates the spin rate and phase of the spinning portion from the inertial attitude reference time of arrival, estimates the relative spin rate and phase between the spinning portion and the despun portion from the index reference time of arrival, and estimates the bearing friction bias torque on the motor means which controls the pointing direction of the despun portion of the spacecraft. The spinning portion spin rate and phase estimates are added with the relative spin rate and phase estimates to produce an estimate of the despun portion spin rate and phase, and the despun portion spin rate and phase estimates and the friction bias torque estimates are subtracted from commanded despun portion spin rate, phase and friction bias torque states. A torque command is generated for controlling the motor means from the subtracted estimates.
摘要翻译：一种双旋转航天器的指示装置，其利用第一传感器，用于在飞行器的旋转部旋转时感测惯性姿态基准的到达时间;以及第二传感器，用于感测索引基准的到达时间，剥离部分与纺纱部分的位置。数字处理器从惯性姿态基准到达时间估计纺丝部分的旋转速度和相位，从指数参考到达时间估计纺纱部分和脱模部分之间的相对旋转速率和相位，并估计轴承摩擦电动机装置上的偏置扭矩，其控制航天器的去除部分的指示方向。旋转部分旋转速率和相位估计值加上相对旋转速率和相位估计值，以产生脱泡部分旋转速率和相位的估计，并且从命令中减去脱泡部分旋转速率和相位估计值和摩擦偏置扭矩估计值绝缘部分旋转速率，相位和摩擦偏置扭矩状态。产生用于从减去的估计值来控制电动机装置的转矩指令。

8. 发明授权

US07681841B2 Method and system for spacecraft power acquisition using single-axis slit sun sensor 有权
标题翻译：使用单轴狭缝太阳传感器进行航天器功率采集的方法和系统
公开(公告)号：US07681841B2
公开(公告)日：2010-03-23
申请号：US11608140
申请日：2006-12-07
申请人： Hanching Grant Wang , Sadek W. Mansour , Douglas J. Bender
发明人： Hanching Grant Wang , Sadek W. Mansour , Douglas J. Bender
IPC分类号： B64G1/36
CPC分类号： B64G1/363 , B64G1/44 , G01S3/7862
摘要： A method for spacecraft power acquisition is provided using single-axis slit sun sensors for both wing-stowed and wing-deployed spacecraft configurations. The method for wing-deployed spacecraft includes initializing a solar wing of the spacecraft to search for sun; rotating the spacecraft about a search axis substantially parallel to a slit sun sensor field of view; monitoring the slit sun sensor for a time of arrival signal; and wherein, if the time of arrival signal occurs, the spacecraft is rotated along the search axis to an orientation where the time of arrival signal occurred and the spacecraft is placed in stable rotation about an axis substantially parallel to a solar wing longitudinal axis; and for a non-occurrence of the time of arrival signal, the spacecraft is slewed about a keyhole axis substantially perpendicular to the search axis to move the sun away from a keyhole.
摘要翻译：使用单轴狭缝太阳传感器提供飞行器功率采集的方法，用于机翼收起和机翼部署的航天器配置。机翼部署的航天器的方法包括初始化太空飞船的太阳能翼，以搜寻太阳; 围绕基本上平行于狭缝太阳传感器视场的搜索轴旋转航天器; 监测狭缝太阳传感器的到达时间信号; 并且其中，如果到达时间信号发生，则航天器沿着搜索轴旋转到出现时间到达信号的方向，并且航天器围绕基本上平行于太阳翼纵向轴线的轴线被稳定地旋转; 并且为了不发生到达时间信号，航天器围绕基本上垂直于搜索轴线的键孔轴旋转，以将太阳从锁孔移开。

9. 发明授权

US6021979A Sun-referenced safe-hold control for momentum biased satellites 失效
标题翻译：用于动量偏移卫星的太阳参考安全保持控制
公开(公告)号：US6021979A
公开(公告)日：2000-02-08
申请号：US94631
申请日：1993-07-19
申请人： Douglas J. Bender , William A. Nakano , William L. Burkett , Kenneth R. Obert , Tiffany Bowles , Stuart F. Bockman
发明人： Douglas J. Bender , William A. Nakano , William L. Burkett , Kenneth R. Obert , Tiffany Bowles , Stuart F. Bockman
IPC分类号： B64G1/24 , B64G1/28 , B64G1/36 , B64G1/44 , G05D1/08
CPC分类号： G05D1/0883 , B64G1/24 , B64G1/285 , B64G1/36 , B64G1/363 , B64G1/365 , B64G1/288 , B64G1/44 , B64G2001/245
摘要： A sun-referenced safe-hold control system for momentum-biased satellites employs a safe-hold processor responsive to a set of sun sensors to detect attitude errors of the solar wings. Safe-hold processor provides independent control logic which rotates the solar wings to ensure that sunlight is maintained incident on the solar wings to maintain solar power in the safe-hold mode. In addition, the safe-hold processor provides independent control of the momentum wheel to place the spacecraft body in a passively stable nutational state. Passive nutational stability inherent in a momentum-biased satellite about two axes of the spacecraft enables the safe-hold processor to actively control the spacecraft about only one of its axes. The spacecraft safe-hold control system increases the period in which spacecraft health is guaranteed by adding active, closed-loop control of the solar wings.
摘要翻译：用于动量偏置卫星的太阳参照的保持控制系统采用响应于一组太阳传感器的安全保持处理器来检测太阳能翼的姿态误差。安全保持处理器提供独立的控制逻辑，其旋转太阳能翼，以确保阳光保持入射到太阳能翼上，以将太阳能发电保持在安全保持模式。此外，安全保持处理器提供对动量轮的独立控制，以将飞船身体置于被动稳定的营养状态。围绕航天器两个轴的动量偏差卫星所固有的被动的营养稳定性使安全保持处理器能够主动地控制航天器只有其中一个轴。航天器安全控制系统通过增加太阳能翼的主动闭环控制，增加了航天器健康的保证期。

10. 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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