公开(公告)号：US06304799B1

公开(公告)日：2001-10-16

申请号：US09510625

申请日：2000-02-22

申请人： Raymond K. DeLong

发明人： Raymond K. DeLong

IPC分类号： B64G136

CPC分类号： H04B10/118 ,  B64G1/36 ,  B64G1/361 ,  B64G1/66

摘要： An apparatus for determining the pointing uncertainty of a satellite communications system comprises a communications terminal coupled to a pointing mechanism which is operative to move and position the communications mechanism. A data storage device is configured to store data from which an actual position of a preselected light source which radiates a reference light can be determined. An acquisition sensor is positioned to move with the communications terminal and is configured to focus incident light onto the acquisition sensor. A control mechanism is coupled to the pointing mechanism and is operative to move the pointing mechanism to a position which would focus the reference light source at a preselected position on the acquisition sensor if the pointing uncertainty were substantially zero. The reference light focusing at a measured position on the acquisition sensor. A processor is coupled to the acquisition sensor and is operative to calculate the difference between the preselected position and the measured position, whereby the pointing uncertainty is calculable from the difference.

摘要翻译： 用于确定卫星通信系统的指向不确定性的装置包括耦合到指向机构的通信终端，其可操作以移动和定位通信机制。 数据存储装置被配置为存储可以从其中确定放射参考光的预选光源的实际位置的数据。 采集传感器被定位成与通信终端一起移动并且被配置成将入射光聚焦到采集传感器上。 控制机构连接到指示机构并且可操作以将指示机构移动到将参考光源聚焦在采集传感器上的预选位置的位置，如果指示不确定度基本上为零。 参考光聚焦在采集传感器上的测量位置。 处理器耦合到采集传感器，并且可操作地计算预选位置与测量位置之间的差值，从而可根据差值来计算指示不确定度。

公开(公告)号：US06460809B1

公开(公告)日：2002-10-08

申请号：US09769637

申请日：2001-01-25

申请人： Yeong-Wei Wu ,  Rongsheng Li ,  James H. Green

发明人： Yeong-Wei Wu ,  Rongsheng Li ,  James H. Green

IPC分类号： B64G136

CPC分类号： G05D1/0883 ,  B64G1/26 ,  B64G1/288 ,  B64G1/361 ,  B64G2001/245

摘要： Structures and methods are provided for deriving corrected star coordinates Ccrctd from measured star coordinates Cms that include star tracker charge transfer efficiency (CTE) errors. The structures and methods are based on a recognition that measured star coordinates Cms of star image centroids include CTE errors which are functions of the CCD path lengths over which the associated electrical charges traveled. In particular, the errors are substantially a product of a respective path length and a star-coordinate error factor &xgr; which, in turn, is a function of the star image magnitudes msi. Information contained in different measured star coordinates Cms is organized to facilitate the derivation of an estimate &xgr;* of the star-coordinate error factor &xgr; with conventional estimation processes. The measured star coordinates Cms are then corrected with the error factor estimate &xgr;* to realize the corrected star coordinates Ccrctd and, thereby, improve the accuracy of spacecraft attitude control.

摘要翻译： 提供了结构和方法，用于从包括星形跟踪器电荷转移效率（CTE）误差的测量的星座坐标Cms导出校正星座标Ccrctd。 结构和方法基于识别，星形图像质心的测量星座坐标Cms包括作为相关电荷行进的CCD路径长度的函数的CTE误差。 特别地，误差基本上是相应的路径长度和星坐标误差因子＆xgr的乘积; 这又是星形图像幅度msi的函数。 包含在不同测量星座坐标Cms中的信息被组织以便于推导星坐标误差因子＆xgr的估计＆xgr * 与传统的估计过程。 然后用误差因子估计＆xgr *来校正测量的星座Cms，以实现校正的星座Ccrctd，从而提高航天器姿态控制的精度。

公开(公告)号：US06450455B1

公开(公告)日：2002-09-17

申请号：US09756395

申请日：2001-01-08

申请人： John E. Davis

发明人： John E. Davis

IPC分类号： B64G136

CPC分类号： B64G1/365 ,  G02B13/06 ,  G05D1/0883

摘要： An optical sensor includes dual fields of view including a panoramic field of view spanning 360° in azimuth angle in a direction perpendicular to an axis of the sensor, and a limb-looking field of view non-perpendicular to the axis for viewing the limb of the earth. Both fields of view are imaged onto annular regions of one of more focal plane arrays comprising pixels arranged in a rectangular array of rows and columns. The sensor is used in a method for capturing rate and direction of rotation of a satellite about its axes and for detecting orientation of the satellite about two of its axes. Rate and direction are determined by finding the center of the earth relative to axes of the focal plane array based on the image of the earth limb from the panoramic field of view, and comparing the earth center location at a series of sequential times. The rate and position information are used for stabilizing an initially tumbling satellite after tip-off. Once the satellite is stabilized, its orientation is detected by finding the earth center location on the focal plane array based on the earth limb image from the limb-looking optics of the sensor. In one embodiment of the invention, both fields of view are imaged onto concentric inner and outer ring-shaped regions of the same focal plane array.

摘要翻译： 光学传感器包括双视野，包括在垂直于传感器的轴线的方向上跨越360°方位角的全景视场，以及不垂直于轴的四肢视野，用于观察肢体的肢体 地球。 这两个视野被成像到包括以行和列的矩形阵列排列的像素的多个焦平面阵列之一的环形区域上。 传感器用于捕获卫星围绕其轴的旋转速度和方向的方法，并用于检测卫星绕其两个轴线的方位。 速率和方向是通过根据全景视野的地球肢体图像，找到相对于焦平面阵列的轴线的地球中心，并在一系列连续时间上比较地球中心位置来确定的。 速率和位置信息用于稳定最终翻滚的卫星。 一旦卫星稳定下来，通过根据传感器肢体光学元件的地球肢体图像，在焦平面阵列上找到地球中心位置来检测其方位。 在本发明的一个实施例中，两个视野都被成像到相同焦平面阵列的同心的内圈和外圈区域上。

公开(公告)号：US06685142B1

公开(公告)日：2004-02-03

申请号：US09583340

申请日：2000-05-31

申请人： Walter Fichter ,  Ernst Brüderle

发明人： Walter Fichter ,  Ernst Brüderle

IPC分类号： B64G136

CPC分类号： G05D1/0883 ,  B64G1/26 ,  B64G1/283 ,  B64G1/285 ,  B64G1/32 ,  B64G1/363 ,  B64G1/365 ,  B64G1/366 ,  B64G2001/245

摘要： A three-axis attitude control for a low-orbiting satellite. A sensor which measures in two axes is a magnetometer, and a satellite is positioned on an inclined orbit at an inclination angle of approximately 25 degrees to approx. 90 degrees. The satellite has been provided with an overall spin by spin wheels, and actuators generate torque on all three axes of the satellite. Accordingly, this is applicable to three-axis attitude control of a low-orbiting satellite that includes a sensor which measures in two axes and that includes one or several spin wheels.

摘要翻译： 用于低轨道卫星的三轴姿态控制。 在两个轴上测量的传感器是磁力计，卫星以大约25度至大约25度的倾斜角位于倾斜轨道上。 90度。 卫星已经通过旋转轮提供整体旋转，并且执行器在卫星的所有三个轴上产生扭矩。 因此，这适用于包括测量两轴并且包括一个或多个旋转轮的传感器的低轨道卫星的三轴姿态控制。

公开(公告)号：US06629672B1

公开(公告)日：2003-10-07

申请号：US10092636

申请日：2002-03-08

申请人： Neil Evan Goodzeit ,  Xipu Li

发明人： Neil Evan Goodzeit ,  Xipu Li

IPC分类号： B64G136

CPC分类号： B64G1/363 ,  B64G1/365 ,  G05D1/0883

摘要： A method for correcting differences in measurements between sensors. Misalignment of a roll error of a sun sensor alignment is estimated with respect to a reference roll value measured by an earth sensor. Sun sensor assembly elevation angle residual is calculated utilizing the estimated sun sensor assembly roll misalignment. A yaw attitude of the spacecraft is updated based upon the calculated sun sensor assembly elevation residual.

摘要翻译： 一种用于校正传感器之间的测量差异的方法。 相对于由地球传感器测量的参考滚动值估计太阳传感器对准的滚动误差的未对准。 使用估计的太阳传感器组件辊未对准来计算太阳传感器组件仰角残差。 基于计算出的太阳传感器组件仰角残差来更新航天器的偏航姿态。

公开(公告)号：US06227496B1

公开(公告)日：2001-05-08

申请号：US09610603

申请日：2000-07-05

申请人： Shoji Yoshikawa ,  Katsuhiko Yamada ,  Hiroshi Sakashita ,  Hiroo Yonechi

发明人： Shoji Yoshikawa ,  Katsuhiko Yamada ,  Hiroshi Sakashita ,  Hiroo Yonechi

IPC分类号： B64G136

CPC分类号： G05D1/0883 ,  B64G1/24 ,  B64G1/288 ,  B64G1/36 ,  B64G1/361 ,  G01C21/025

摘要： An attitude determination system for an artificial satellite capable of performing star identification without need for the aid of ground station includes an image processing module (17) for processing star images observed at predetermined time points by a star sensor (16) mounted on the artificial satellite (1) for arithmetically determining direction vectors of the observed stars, a rotation estimating module (18) for estimating a rotational motion of the artificial satellite (1) between an attitude of the artificial satellite at a predetermined time point and an attitude of the artificial satellite at another time point, an elongation estimating module (19) for estimating elongations between the direction vectors of plural stars the images of which are picked up at a same time point by the star sensor and estimating the elongations between the direction vectors of plural stars the images of which are picked up at different time points by the star sensor on the basis of the estimated rotational motion, a star identifying module (20) for establishing correspondences between a plurality of the stars for which relation of the elongation has been determined and stars on a star catalog for identifying the stars, and an attitude angle estimating module (21) for estimating an attitude angle of the artificial satellite on the basis of result of identification of the stars.

摘要翻译： 能够在不需要地面站的帮助下进行星型识别的人造卫星的姿势确定系统包括：图像处理模块（17），用于处理在预定时间点由安装在人造卫星上的星形传感器（16）观察到的星形图像 （1），用于对所述观测星的方向矢量进行算术确定;旋转估计模块，用于估计所述人造卫星在预定时间点的姿态与人造卫星的姿态之间的旋转运动; 卫星在另一个时间点，延伸率估计模块（19），用于估计多个恒星的方向向量之间的延伸，其中图像由星形传感器在同一时间点被拾取并且估计多个恒星的方向向量之间的伸长 其基于估计的星形传感器在不同时间点拾取图像 旋转运动的星形识别模块（20），用于在已经确定了伸长关系的多个星星之间建立对应关系，并且用于识别恒星的星形目录上的恒星;以及姿态角估计模块（21），用于估计 人造卫星的姿态角基于星星识别的结果。

公开(公告)号：US06588708B2

公开(公告)日：2003-07-08

申请号：US09771916

申请日：2001-01-29

申请人： Grant Wang ,  Yeong-Wei Wu ,  Rongsheng Li ,  David D. Needelman

发明人： Grant Wang ,  Yeong-Wei Wu ,  Rongsheng Li ,  David D. Needelman

IPC分类号： B64G136

CPC分类号： B64G1/361 ,  B64G1/428 ,  B64G1/44

摘要： The present invention is directed to spacecraft that have, for any reason, lost the spacecraft's service attitude that permits it to carry out the service operations for which it was designed. The invention provides methods and structures for acquiring and determining a power-safe attitude (i.e., one in which wing current is sufficient to support the spacecraft's housekeeping operations) from which the spacecraft can be subsequently returned to a service attitude. The methods are particularly useful because they a) require only a single star tracker for sensing attitude, comprise simple maneuvers, and typically acquire a power-safe attitude that does not significantly differ from the spacecraft's service attitude to thereby reduce the spacecraft's return-to-service time.

摘要翻译： 本发明涉及由于任何原因丢失航天器的服务态度而允许其执行其设计的服务操作的航天器。 本发明提供了用于获取和确定动力安全姿态（即其中机翼电流足以支持航天器内务处理操作）的方法和结构，由此航天器可随后返回到服务态度。 这些方法特别有用，因为它们只需要一个单一的星形跟踪器来感测姿态，包括简单的操作，并且通常获得与航天器的服务态度没有显着差异的电力安全姿态，从而减少航天器的返回 - 服务时间。

公开(公告)号：US06561462B1

公开(公告)日：2003-05-13

申请号：US10081468

申请日：2002-02-21

申请人： Hanching G. Wang ,  Umesh Ketkar ,  Albert A. Munoz ,  Sadek Mansour

发明人： Hanching G. Wang ,  Umesh Ketkar ,  Albert A. Munoz ,  Sadek Mansour

IPC分类号： B64G136

CPC分类号： B64G1/363 ,  B64G2001/245

摘要： A spacecraft power/sun acquisition method includes a pitch search phase in which the spacecraft is rotated about a pitch axis, stopped, quaternions reset to remember position, and yaw search phase is entered when a first TOA occurs from a first slit sun sensor, and a keyhole slew is performed when the first TOA does not occur. The method also includes yaw search phase in which a keyhole slew is performed by rotating the spacecraft about a yaw axis, stopping the spacecraft, and entering pitch search phase when the first TOA does not occur, and in which the spacecraft is rotated about a yaw axis, stopped, quaternions reset, and sun hold phase is entered when a second TOA occurs from a second slit sun sensor. Lastly, the method includes a sun hold phase in which the spacecraft is oriented to the sun and placed in spin at power safe attitude.

摘要翻译： 航天器功率/太阳采集方法包括：俯仰搜索阶段，其中航天器围绕俯仰轴线旋转，停止，四元数复位为记忆位置，并且当第一狭缝太阳传感器发生第一TOA时进入偏航搜索阶段，以及 当不发生第一个TOA时执行锁孔旋转。 该方法还包括偏航搜索阶段，其中通过围绕偏转轴旋转航天器，停止航天器并且当第一TOA不发生时进入俯仰搜索阶段执行锁孔，并且其中航天器围绕偏航旋转 轴，停止，四元数复位，并且当从第二狭缝太阳传感器发生第二TOA时进入太阳保持相位。 最后，该方法包括太阳保持阶段，其中航天器被定向到太阳并以功率安全的姿态旋转。

公开(公告)号：US06478260B1

公开(公告)日：2002-11-12

申请号：US09507099

申请日：2000-02-17

申请人： Christopher L. Rice ,  Yeong-Wei A. Wu

发明人： Christopher L. Rice ,  Yeong-Wei A. Wu

IPC分类号： B64G136

CPC分类号： G01C21/025 ,  B64G1/361 ,  G01S3/781 ,  G01S3/7867 ,  G01S5/0247

摘要： An apparatus for determining star location includes a star tracker, a star catalog and a controller. The star tracker is used to sense the positions of stars and generate signals corresponding to the positions of the stars as seen in its field of view. The star catalog contains star location data that is stored using a primary and multiple secondary arrays sorted by both declination (DEC) and right ascension (RA), respectively. The controller checks the star catalog and determines which stars to track. The controller does this determination by using an algorithm to sort the primary and secondary arrays to determine which stars are located in the star tracker field of view. The controller then commands the star tracker to track these stars and uses them to determine the spacecraft attitude.

摘要翻译： 用于确定星形位置的装置包括星形跟踪器，星形目录和控制器。 星形跟踪器用于感测恒星的位置，并产生与其视场中所见的恒星位置相对应的信号。 星型目录包含使用分别由偏角（DEC）和右升高（RA）排序的主要和多个辅助阵列存储的星形位置数据。 控制器检查星型目录并确定要跟踪哪些恒星。 控制器通过使用算法对主阵列和辅助阵列进行排序来确定哪些恒星位于星型跟踪器视野中来执行此确定。 然后，控制器命令星形跟踪器跟踪这些恒星并使用它们来确定航天器的姿态。

公开(公告)号：US06310336B1

公开(公告)日：2001-10-30

申请号：US09150560

申请日：1998-09-10

申请人： Cary J. Abul-Haj ,  Thomas R. Parks

发明人： Cary J. Abul-Haj ,  Thomas R. Parks

IPC分类号： B64G136

CPC分类号： B64G1/363 ,  G01C21/24 ,  G01S3/781 ,  G01S5/163

摘要： The present invention is embodied in an apparatus for sensing solar position. The apparatus includes a precision wide-field-of-view (WFOV) passive optical sensor head and a set of interface electronics disposed within a spacecraft computer, which is located remotely from the precision WFOV optical sensor head. The interface electronics convert current signals supplied by the precision WFOV optical sensor head into digital signals usable by a spacecraft control processor. The spacecraft control processor uses the digital signals from the interface electronics to precisely determine the attitude of the spacecraft.

摘要翻译： 本发明体现在用于感测太阳位置的装置中。 该装置包括精密宽视场（WFOV）无源光学传感器头和设置在远离精密WFOV光学传感器头的航天器计算机内的一组接口电子设备。 接口电子器件将由精密WFOV光学传感器头提供的电流信号转换成可被航天器控制处理器使用的数字信号。 航天器控制处理器使用来自接口电子设备的数字信号来精确地确定航天器的姿态。