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公开(公告)号：US5738309A
公开(公告)日：1998-04-14
申请号：US608238
申请日：1996-02-28
申请人： Richard A. Fowell
发明人： Richard A. Fowell
摘要： A method and system of orienting a payload of an orbiting spacecraft (14) to maintain a desired pointing profile in the presence of orbit inclination. A cone (12) is determined which is traced in inertial space by a pitch axis of the payload to maintain the desired pointing profile throughout an orbit. A bias momentum vector of the spacecraft (14) is oriented at an attitude which lies along the cone (12). The attitude has a nonzero angle with respect to a plane spanned by an orbit normal vector and an equatorial normal vector. The payload is rotated about a single body-fixed axis perpendicular to the pitch axis to align the pitch axis along the cone (12). As a result, the desired pointing profile is maintained throughout the inclined orbit.
摘要翻译： 定向轨道航天器（14）的有效载荷以在存在轨道倾斜的情况下维持期望的指向轮廓的方法和系统。 确定锥体（12），其通过有效负载的俯仰轴在惯性空间中跟踪以在整个轨道中保持期望的指向轮廓。 航天器（14）的偏压动量向量定位成位于锥体（12）处的姿态。 姿态相对于由轨道法线向量和赤道法线向量横跨的平面具有非零的角度。 有效载荷围绕垂直于俯仰轴线的单个主体固定轴线旋转，以使俯仰轴线沿着锥体（12）对准。 结果，在整个倾斜的轨道上保持期望的指向轮廓。
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公开(公告)号：US08041118B2
公开(公告)日：2011-10-18
申请号：US11707674
申请日：2007-02-16
申请人： Richard A. Fowell
发明人： Richard A. Fowell
IPC分类号： G06K9/00
CPC分类号： B64G1/361 , B64G1/1007 , G06K9/00087 , G06K9/00617 , G06K9/6211
摘要： In an exemplary embodiment, a pattern is recognized from digitized images. A first image metric is computed from a first digitized image and a second image metric is computed from a second digitized image. A composite image metric is computed as a function of the first image metric and the second image metric, and a pattern is identified by comparing the composite image metric against a reference image metric. The function may be a simple average or a weighted average. The image metric may include a separation distance between features, or a measured area of a feature, or a central angle between two arcs joining a feature to two other features, or an area of a polygon whose vertices are defined by features, or a second moment of a polygon whose vertices are defined by features. The images may include without limitation images of friction ridges, irises, or stars.
摘要翻译： 在示例性实施例中，从数字化图像识别图案。 从第一数字化图像计算第一图像度量，并且从第二数字化图像计算第二图像度量。 作为第一图像度量和第二图像度量的函数计算合成图像度量，并且通过将合成图像度量与参考图像度量进行比较来识别图案。 该函数可以是简单的平均值或加权平均值。 图像度量可以包括特征之间的间隔距离，或特征的测量区域，或将特征连接到两个其他特征的两个弧之间的中心角，或其顶点由特征定义的多边形的区域，或第二 顶点由特征定义的多边形的时刻。 图像可以包括但不限于摩擦脊，虹膜或星星的图像。
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13.发明授权Method and apparatus for reducing quantization-induced beam errors by selecting quantized coefficients based on predicted beam quality 有权用于通过基于预测的光束质量选择量化系数来减少量化诱发光束误差的方法和装置公开(公告)号：US07274329B2
公开(公告)日：2007-09-25
申请号：US10877883
申请日：2004-06-25
IPC分类号： H01Q3/00
CPC分类号： H04B7/2041 , H01Q3/267
摘要： A method and apparatus for correcting a beam error is disclosed. One embodiment of the method comprises the steps of selecting beamweight coefficients based on the satellite orbital data, evaluating an effect of quantization of the beamweight coefficients on the beam error, and selecting beamweight coefficients based at least in part upon the evaluation of the effect of beamweight coefficient quantization on beam error. One embodiment of the apparatus comprises a beamweight correction module for selecting beamweight coefficients based on satellite orbital data, for evaluating the effect of quantization of the beamweight coefficients on beam error, and for selecting beamweight coefficients based at least in part upon the evaluation of the effect of beamweight coefficient quantization on beam error. The beamweight correction module comprises a beamweight generator and a beamweight quantizer for quantizing beamweights from the beamweight generator.
摘要翻译： 公开了一种用于校正光束误差的方法和装置。 该方法的一个实施例包括以下步骤：基于卫星轨道数据选择波束权重系数，评估波束权重系数的量化对波束误差的影响，以及至少部分地基于对波束权重的影响的评估来选择波束权重系数 波束误差系数量化。 该装置的一个实施例包括用于基于卫星轨道数据选择波束权重系数的波束权重校正模块，用于评估波束权重系数的量化对波束误差的影响，以及至少部分地基于对该效应的评估来选择波束权重系数 的束权系数量化对波束误差的影响。 光束重量校正模块包括光束重量发生器和用于量化来自光束重量发生器的光束重量的光束权重量化器。
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14.发明授权Method and apparatus for correction of quantization-induced beacon beam errors 有权用于校正量子化信标光束误差的方法和装置公开(公告)号：US07268726B2
公开(公告)日：2007-09-11
申请号：US10877564
申请日：2004-06-25
摘要： A method of correcting for beacon pointing errors is disclosed. A desired beacon value and a predicted measured beacon value are computed and used to generate the beacon correction. An antenna pattern calculator can be used to compute the predicted measured beacon value, and a beacon correction value generator can be used to compute the desired beacon value and to generate the beacon correction.
摘要翻译： 公开了一种校正信标指向误差的方法。 计算期望的信标值和预测的测量信标值，并用它来产生信标校正。 可以使用天线方向图计算器来计算预测的测量信标值，并且可以使用信标校正值发生器来计算所需的信标值并产生信标校正。
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15.发明授权公开(公告)号：US06293502B1
公开(公告)日：2001-09-25
申请号：US09368202
申请日：1999-08-04
申请人： Richard A. Fowell
发明人： Richard A. Fowell
IPC分类号： B64G124
摘要： A satellite (30) programmed for sun-nadir steering and having a solar wing (36) mounted to the satellite body (35) and being selectively moveable about two mutually orthogonal axes (A, B). The solar wing (36) is mounted to the satellite body (35) by a pair of gimbals (43, 45) thus allowing two degrees of freedom and thereby permitting the solar wing (36) to be rotated about the two mutually orthogonal axes (A, B). A first motor (42) in operative engagement with the gimbal (43) selectively rotates the solar wing about the axis (A), while a second motor (46) in operative engagement with the gimbal (45) selectively rotates the solar wing about the second axis (B). A control circuit (40) is in operative engagement with the first and second motors and selectively causes the first motor to rotate the solar wing about the first axis to a predetermined position, and selectively causes the second motor to rotate the solar wing about the second axis to a predetermined position.
摘要翻译： 一个被编程用于太阳天底转向的卫星（30），并具有安装在卫星本体（35）上的太阳翼（36），并且可围绕两个相互正交的轴线（A，B）移动。 太阳能翼（36）通过一对万向节（43,45）安装到卫星体（35），从而允许两个自由度，从而允许太阳能翼（36）围绕两个相互正交的轴线（ A，B）。 与万向节（43）可操作地接合的第一马达（42）选择性地围绕轴线（A）旋转太阳能飞轮，而与万向节（45）有效接合的第二马达（46）选择性地使太阳能飞轮围绕 第二轴（B）。 控制电路（40）与第一和第二电动机可操作地接合，并选择性地使第一电动机将太阳能翼绕第一轴线旋转到预定位置，并且选择性地使第二电动机围绕第二电动机 轴到预定位置。
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公开(公告)号：US5884869A
公开(公告)日：1999-03-23
申请号：US617230
申请日：1996-03-18
摘要： A method for simultaneously controlling satellite nutation, sun angle and attitude walk using a dual-slit sun sensor and thrusters. The sun angle and nutation angles are computed from sun sensor data, and the thrusters are fired when their use improves both sun angle and nutation. Precession around the sun line is controlled by constraining firing, in the simplest case, firing only when the angular momentum is precessed directly toward or away from the sun. Precession maneuvers are implemented by commanding a new sun angle and precession plane spin phase.
摘要翻译： 使用双缝太阳传感器和推进器同时控制卫星章动，太阳角和姿态走路的方法。 太阳角和章动角由太阳传感器数据计算，推进器在使用时改善太阳角和章动，发射。 围绕太阳线的过程由限制射击控制，在最简单的情况下，只有当角动量直接进入太阳或远离太阳时才进行射击。 通过指挥新的太阳角和进动平面自旋相来实现进动机动。
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公开(公告)号：US5826828A
公开(公告)日：1998-10-27
申请号：US597083
申请日：1996-02-05
摘要： Methods for performing attitude maneuvers of a spinning satellite without the use of thrusters, or with a minimal number of thrusters, are disclosed. The attitude maneuvers are primarily achieved through the use of gimballed momentum wheels and solar wing drives. Various maneuvers can be performed depending on whether the satellite has near-zero net momentum or significant net momentum. The maneuvers include sun acquisition, sun hold, Earth acquisition and inversion.
摘要翻译： 公开了在不使用推进器或最少数量的推进器的情况下进行旋转卫星的姿态机动的方法。 态度演绎主要是通过使用金球动力轮和太阳能翼驱动来实现的。 可以根据卫星是否接近零净动量或显着的净动量来执行各种演习。 演习包括太阳采集，太阳持续，地球捕获和反演。
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18.发明授权Method and apparatus for reaction wheel dynamic compensation in long-duration deployment of a large reflector 失效大反射镜长时间部署中反作用轮动态补偿的方法和装置公开(公告)号：US06990396B2
公开(公告)日：2006-01-24
申请号：US10318867
申请日：2002-12-13
IPC分类号： G06F7/00
CPC分类号： B64G1/24 , B64G1/26 , B64G1/281 , B64G1/283 , B64G1/285 , B64G1/288 , B64G1/361 , B64G1/363 , B64G1/366
摘要： A method and an apparatus for controlling the attitude and momentum of a spacecraft while deploying an appendage from the spacecraft. The method comprises the steps of predicting an environmental torque the spacecraft will be subjected to during deployment of the appendage, computing a magnitude and a direction of momentum to add to the spacecraft to at least partially oppose the predicted environmental torque, and storing the computed magnitude and direction of momentum in at least one of the momentum wheels before deploying the appendage.
摘要翻译： 一种用于在从航天器部署附件的同时控制航天器的姿态和动量的方法和装置。 该方法包括以下步骤：在部署附件期间预测航天器将遭受的环境扭矩，计算增加到航天器的动量的大小和方向以至少部分地反对预测的环境转矩，并且存储所计算的大小 并且在部署附件之前至少有一个动量轮的动量方向。
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公开(公告)号：US06978966B2
公开(公告)日：2005-12-27
申请号：US10770903
申请日：2004-02-02
CPC分类号： H01Q15/147 , B64G1/222 , B64G1/66 , H01Q1/288
摘要： A system and method for performing in-orbit alignment calibration using on-board attitude sensors to improve reflector alignment after deployment to improve spacecraft pointing.
摘要翻译： 一种用于使用车载姿态传感器执行轨道内对准校准的系统和方法，以在部署之后改善反射器对准以改善航天器指向。
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公开(公告)号：US06863244B2
公开(公告)日：2005-03-08
申请号：US10360020
申请日：2003-02-07
申请人： Richard A. Fowell , Salma I. Saeed , Rongsheng Li , Yeong-Wei Wu
发明人： Richard A. Fowell , Salma I. Saeed , Rongsheng Li , Yeong-Wei Wu
摘要： A method, apparatus, article of manufacture, and a memory structure for compensating for optical sensor data corrupted by angular acceleration is disclosed. The method comprises the steps of determining an angular acceleration of the optical sensor and modifying the optical sensor data according to the determined angular acceleration of the optical sensor. The apparatus comprises a sensor for determining an angular acceleration of the optical sensor and a navigation system for modifying the optical sensor data according to the determined angular acceleration of the optical sensor.
摘要翻译： 公开了一种用于补偿由角加速度损坏的光学传感器数据的方法，装置，制品和存储结构。 该方法包括以下步骤：根据确定的光学传感器的角加速度确定光学传感器的角加速度并修改光学传感器数据。 该装置包括用于确定光学传感器的角加速度的传感器和用于根据确定的光学传感器的角加速度来修改光学传感器数据的导航系统。
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