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81. 发明授权

US5758846A Satellite spin inversion using a single degree of freedom momentum storage device 失效
标题翻译：卫星自旋反转采用单自由度动量储存装置
公开(公告)号：US5758846A
公开(公告)日：1998-06-02
申请号：US816727
申请日：1997-03-13
申请人： Richard A. Fowell
发明人： Richard A. Fowell
IPC分类号： B64G1/24 , B64G1/28 , B64G1/36 , B64G1/38 , G05D1/08
CPC分类号： B64G1/24 , B64G1/281 , B64G1/285 , B64G1/288 , B64G1/36 , B64G1/38 , G05D1/0883 , B64G1/283 , B64G1/286 , B64G1/361 , B64G1/363 , B64G1/365
摘要： A method and system are disclosed for inverting a satellite spinning about a first desired spin axis to spin about a second desired spin axis substantially antiparallel to the first desired spin axis. A tumbling motion is induced in the satellite so that a spin axis of the satellite oscillates between the first desired spin axis and the second desired spin axis. The tumbling motion is induced by sensing at least one component of the angular rate vector and controlling a single degree of freedom momentum storage device based upon the at least one component of the angular rate vector. The single degree of freedom momentum storage device has an orientation of variation substantially perpendicular to the desired spin axis. The single degree of freedom momentum storage device is controlled so that the first desired spin axis is made an intermediate inertia axis of an effective inertia matrix. A capture point is detected at which the angular rate vector is sufficiently close to the second desired spin axis to be recaptured. After detecting the capture point, the single degree of freedom momentum storage device is controlled so that the angular rate vector substantially aligns with the second desired spin axis.
摘要翻译：公开了一种方法和系统，用于颠倒围绕第一期望自旋轴的卫星旋转，以围绕基本上反平行于第一所需旋转轴的第二期望自旋轴旋转。在卫星中引起滚动运动，使得卫星的旋转轴在第一期望旋转轴和第二所需旋转轴之间振荡。通过感测角速率矢量的至少一个分量并且基于角速率矢量的至少一个分量来控制单个自由度动量存储装置来感应翻滚运动。单自由度动量存储装置具有基本上垂直于期望旋转轴的变化方向。控制单自由度动量存储装置，使得第一期望旋转轴成为有效惯性矩阵的中间惯性轴。检测捕获点，其中角速度矢量足够接近第二期望的旋转轴以被重新捕获。在检测到捕获点之后，控制单个自由度动量存储装置，使得角速度矢量基本上与第二期望的旋转轴对齐。

82. 发明授权

US5758260A Satellite beam steering reference using terrestrial beam steering terminals 失效
标题翻译：卫星波束转向参考使用地面波束转向终端
公开(公告)号：US5758260A
公开(公告)日：1998-05-26
申请号：US518524
申请日：1995-08-23
申请人： Robert A. Wiedeman
发明人： Robert A. Wiedeman
IPC分类号： B64G1/10 , B64G1/24 , B64G1/36 , B64G1/66 , B64G3/00 , G05D1/08 , H04B7/195 , H04B7/204 , H04B7/216 , H04B7/185
CPC分类号： H04B7/2041 , B64G1/24 , B64G1/363 , B64G1/365 , B64G1/366 , B64G3/00 , G05D1/0883 , B64G1/1007 , B64G1/66
摘要： A satellite communication system has at least one satellite (1) with an antenna that generates a moving beam pattern on the surface of the earth. The beam pattern (3) is comprised of a plurality of sub-beams (4). A method of this invention determines an attitude correction signal for the satellite by the steps of: (a) providing at least one reference transmitter (10) at a known location on the surface of the earth; (b) transmitting at least one signal from the at least reference transmitter into at least one of the sub-beams; (c) receiving the at least one signal with the satellite antenna and transponding the received at least one signal to a ground station (8). A next step of the method (d) receives the transponded at least one signal with the ground station; (e) determines a gain of the received at least one signal; (f) compares the determined gain to a gain expected to be received based on a predetermined knowledge of a spatial variation in gain of the satellite antenna; and (g) and determines a difference between the determined gain and the expected gain to derive a correction signal indicative of an attitude error of the satellite. The method further includes the steps of transmitting the correction signal to the satellite; and correcting the attitude of the satellite in accordance with the correction signal.
摘要翻译：卫星通信系统具有至少一个具有天线的卫星（1），其在地球表面上产生移动的波束图案。光束图案（3）由多个子光束（4）组成。本发明的方法通过以下步骤确定卫星的姿态校正信号：（a）在地球表面上的已知位置提供至少一个参考发射机（10）; （b）将至少一个信号从所述至少参考发射机传送到所述子光束中的至少一个; （c）用所述卫星天线接收所述至少一个信号，并将所接收的至少一个信号转发到地面站（8）。方法（d）的下一步骤接收与地面站的转发的至少一个信号; （e）确定所接收的至少一个信号的增益; （f）基于卫星天线的增益的空间变化的预定知识将所确定的增益与预期接收的增益进行比较; 和（g）并且确定所确定的增益和预期增益之间的差异，以导出指示卫星的姿态误差的校正信号。该方法还包括以下步骤：将校正信号发送到卫星; 以及根据校正信号校正卫星的姿态。

83. 发明授权

US5697582A Method of adjusting the position of satellites by means of solar pressure torques 失效
标题翻译：通过太阳能压力转矩调整卫星位置的方法
公开(公告)号：US5697582A
公开(公告)日：1997-12-16
申请号：US146036
申请日：1994-02-10
申请人： Michael Surauer , Helmut Bittner
发明人： Michael Surauer , Helmut Bittner
IPC分类号： B64G1/24 , B64G1/28 , B64G1/36 , B64G1/40 , B64G1/44 , G05D1/08
CPC分类号： B64G1/24 , B64G1/283 , B64G1/285 , B64G1/407 , B64G1/443 , B64G1/363 , B64G1/44
摘要： A method for adjusting the orientation and for compensating interfering torques via solar pressure torques for a satellite moving on an orbit around the earth. The satellite has two solar generators arranged symmetrically on opposite sides of a main body of the satellite. The two solar generators are rotatable independently of one another via servomotors about a first axis of rotation orthogonal to an orbiting plane of the satellite when the position of the satellite is correct. The method comprises the step of: optionally generating solar pressure torques about at least one of three space axes oriented orthogonally with respect to one another, as a result of an adjustment of the solar generators by a targeted rotation about second axes of rotation orthogonal to the first axis of rotation or about the first axis and the second axes of rotation, with respect to a nominal orientation in which the solar generator's normals to surfaces are precisely aligned in the direction of the sun.
摘要翻译： PCT No.PCT / EP92 / 00995 Sec。 371日期：1994年2月10日 102（e）日期1994年2月10日PCT提交1992年5月7日PCT公布。出版物WO92 / 19498 日期1992年11月12日一种用于通过太阳能压力转矩调整方位和补偿干扰转矩的方法，用于在围绕地球的轨道上移动的卫星。卫星具有对称地布置在卫星主体的相对侧上的两个太阳能发电机。当卫星的位置是正确的时，两个太阳能发电机可以通过伺服电动机彼此独立地彼此旋转，绕第一旋转轴正交于卫星的绕行平面。该方法包括以下步骤：作为通过绕与第二轴正交的第二旋转轴线的目标旋转来调整太阳能发电机的结果，可选地产生围绕彼此正交定向的三个空间轴中的至少一个的太阳能压力扭矩第一旋转轴线或围绕第一轴线和第二旋转轴线相对于其中太阳能发电机的正面与太阳的方向精确对准的标称取向。

84. 发明授权

US5697050A Satellite beam steering reference using terrestrial beam steering terminals 失效
标题翻译：卫星波束转向参考使用地面波束转向终端
公开(公告)号：US5697050A
公开(公告)日：1997-12-09
申请号：US764307
申请日：1996-12-12
申请人： Robert A. Wiedeman
发明人： Robert A. Wiedeman
IPC分类号： B64G1/10 , B64G1/24 , B64G1/36 , B64G1/66 , B64G3/00 , G05D1/08 , H04B7/195 , H04B7/204 , H04B7/216 , H04B7/15
CPC分类号： H04B7/2041 , B64G1/24 , B64G1/363 , B64G1/365 , B64G1/366 , B64G3/00 , G05D1/0883 , B64G1/1007 , B64G1/66
摘要： A satellite communication system has at least one satellite (1) with an antenna that generates a moving beam pattern on the surface of the earth. The beam pattern (3) is comprised of a plurality of sub-beams (4). A method of this invention determines an attitude correction signal for the satellite by the steps of: (a) providing at least one reference transmitter (10) at a known location on the surface of the earth; (b) transmitting at least one signal from the at least reference transmitter into at least one of the sub-beams; (c) receiving the at least one signal with the satellite antenna and transponding the received at least one signal to a ground station (8). A next step of the method (d) receives the transponded at least one signal with the ground station; (e) determines a gain of the received at least one signal; (f) compares the determined gain to a gain expected to be received based on a predetermined knowledge of a spatial variation in gain of the satellite antenna; and (g) and determines a difference between the determined gain and the expected gain to derive a correction signal indicative of an attitude error of the satellite. The method further includes the steps of transmitting the correction signal to the satellite; and correcting the attitude of the satellite in accordance with the correction signal. For the case where the correction signal has a value that is a function of the yaw error angle of the satellite, the method further includes the steps of transmitting the correction signal to the satellite; and correcting the attitude of the satellite in accordance with the correction signal by rotating the satellite about the yaw axis so as to reduce a magnitude of the yaw error angle.
摘要翻译：卫星通信系统具有至少一个具有天线的卫星（1），其在地球表面上产生移动的波束图案。光束图案（3）由多个子光束（4）组成。本发明的方法通过以下步骤确定卫星的姿态校正信号：（a）在地球表面上的已知位置提供至少一个参考发射机（10）; （b）将至少一个信号从所述至少参考发射机传送到所述子光束中的至少一个; （c）用所述卫星天线接收所述至少一个信号，并将所接收的至少一个信号转发到地面站（8）。方法（d）的下一步骤接收与地面站的转发的至少一个信号; （e）确定所接收的至少一个信号的增益; （f）基于卫星天线的增益的空间变化的预定知识将所确定的增益与预期接收的增益进行比较; 和（g）并且确定所确定的增益和预期增益之间的差异，以导出指示卫星的姿态误差的校正信号。该方法还包括以下步骤：将校正信号发送到卫星; 以及根据校正信号校正卫星的姿态。对于校正信号具有作为卫星的偏航误差角的函数的值的情况，该方法还包括将修正信号发送到卫星的步骤; 以及通过围绕所述偏转轴旋转所述卫星来校正所述卫星的姿态，以便减小所述偏航误差角的大小。

85. 发明授权

US5667171A Satellite spin axis stabilization using a single degree of freedom transverse momentum storage device 失效
标题翻译：卫星旋转轴稳定采用单自由度横向动量存储装置
公开(公告)号：US5667171A
公开(公告)日：1997-09-16
申请号：US430636
申请日：1995-04-28
申请人： Richard A. Fowell , John F. Yocum
发明人： Richard A. Fowell , John F. Yocum
IPC分类号： B64G1/24 , B64G1/28 , B64G1/36 , B64G1/38 , G05D1/08
CPC分类号： B64G1/24 , B64G1/281 , B64G1/285 , B64G1/288 , B64G1/36 , B64G1/38 , G05D1/0883 , B64G1/283 , B64G1/286 , B64G1/361 , B64G1/363 , B64G1/365
摘要： Methods and systems for stabilizing satellite spin about an intermediate inertia axis (Z) are disclosed. A set of gyros (22) sense the X component and the Y component of the angular velocity of the satellite body. A single degree of freedom momentum wheel (26) has a fixed transverse orientation with respect to the intermediate axis in order to store momentum. In one embodiment, the momentum wheel (26) is oriented to store momentum parallel to the Y axis. A tachometer (30) senses the rotation rate of the momentum wheel (26). A processor (24) forms a control signal representative of a control torque to be applied to the momentum wheel (26). The control torque is based upon the X component and the Y component of angular velocity of the satellite, and the angular velocity of the momentum wheel (26). These methods and systems may also be used to invert the spin direction of spinning satellites, ensure tumble recover to a preferred orientation, and stabilize the body spin axis against nutation, dynamic imbalance and external torques.
摘要翻译：公开了围绕中间惯性轴（Z）稳定卫星旋转的方法和系统。一组陀螺仪（22）感测卫星体的角速度的X分量和Y分量。单个自由度动量轮（26）相对于中间轴线具有固定的横向取向以便储存动量。在一个实施例中，动量轮（26）被定向成存储平行于Y轴的动量。转速计（30）感测动量轮（26）的旋转速度。处理器（24）形成表示要施加到动量轮（26）的控制扭矩的控制信号。控制扭矩基于卫星的角速度的X分量和Y分量以及动量轮（26）的角速度。这些方法和系统也可以用于反转旋转卫星的旋转方向，确保滚筒恢复到优选的方向，并且使身体旋转轴线抵抗章动，动态不平衡和外部扭矩。

86. 发明授权

US5558305A Measuring arrangement useful for controlling the attitude of a three-axis stabilized satellite, corresponding evaluation process, regulating system and process 失效
标题翻译：用于控制三轴稳定卫星姿态的测量装置，相应的评估过程，调节系统和过程
公开(公告)号：US5558305A
公开(公告)日：1996-09-24
申请号：US204324
申请日：1994-07-27
申请人： Michael Surauer , Helmut Bittner , Walter Fichter , Horst-Dieter Fischer
发明人： Michael Surauer , Helmut Bittner , Walter Fichter , Horst-Dieter Fischer
IPC分类号： B64G1/00 , B64G1/24 , B64G1/28 , B64G1/36 , G05D1/08
CPC分类号： B64G1/363 , B64G1/007 , G05D1/0883 , B64G1/242 , B64G1/288 , B64G1/365 , B64G2001/245
摘要： A measurement arrangement is useful for controlling the attitude of a three-axis stabilized satellite equipped with sun-sensors for determining the orientation of the sun (sun vector) with respect to a satellite-fixed coordinate system, as well as with speed gyroscopes for detecting components of the satellite speed of rotation vector .omega.. It is necessary that the measurement range of the sun-sensors cover the round angle in a preselectable plane (for example XY plane) and perpendicularly thereto a limited angular range of maximum .+-..alpha..sub.2max on both sides of the plane. In addition, only an integrating speed gyroscope carrying out measurements in a single measurement axis that encloses with the plane an angle of at least (.pi./2)-.alpha..sub.2max should be provided. Also disclosed are an evaluation process for determining the satellite speed of rotation, as well as the satellite deviation with respect to a direction of reference, a regulating system for carrying out attitude control maneuvers using the measurement arrangement and the evaluation process, and a corresponding regulating process.
摘要翻译： PCT No.PCT / EP92 / 02051 Sec。 371日期：1994年7月27日 102（e）日期1994年7月27日PCT提交1992年9月4日PCT公布。公开号WO93 / 04923 日期1993年3月18日测量安排对于控制配备有太阳传感器的三轴稳定卫星的姿态有助于确定太阳（太阳矢量）相对于卫星固定坐标系的方向，以及用于检测卫星旋转矢量ω的分量的速度陀螺仪。太阳传感器的测量范围必须覆盖预选平面（例如XY平面）中的圆角并垂直于平面两侧的最大+/- alpha2max的有限角度范围。此外，只应提供在单个测量轴上进行测量的积分速度陀螺仪，该测量轴与平面包围至少（pi / 2）-a2max的角度。还公开了用于确定卫星旋转速度以及相对于参考方向的卫星偏差的评估过程，用于使用测量装置和评估过程执行姿态控制机动的调节系统，以及相应的调节处理。

87. 发明授权

US5556058A Spacecraft attitude determination using sun sensor, earth sensor, and space-to-ground link 失效
标题翻译：使用太阳传感器，地球传感器和空对地链路的航天器姿态测定
公开(公告)号：US5556058A
公开(公告)日：1996-09-17
申请号：US243669
申请日：1994-05-16
申请人： Douglas J. Bender
发明人： Douglas J. Bender
IPC分类号： G01C21/24 , B64G1/24 , B64G1/28 , B64G1/36 , B64G3/00 , G05D1/08
CPC分类号： B64G1/24 , B64G1/285 , B64G1/363 , B64G1/365 , B64G3/00 , G05D1/0883 , B64G2001/245
摘要： A method and system for determining the general three-axis attitude measurement for a spacecraft is disclosed. The system provides a cost-effective attitude measurement system for geosynchronous momentum bias spacecraft which need a continuously updated, moderately accurate, yaw measurement in addition to the usual roll and pitch measurements. The continuous yaw measurement enables control of the spacecraft yaw axis in the presence of disturbance torques. A sun sensor generates a signal which may be used to calibrate a continuously updated yaw measurement derived from the combination of signals generated by an Earth sensor and a space-to-ground link.
摘要翻译：公开了一种用于确定航天器的一般三轴姿态测量的方法和系统。该系统为地面同步动量偏置航天器提供了一种经济高效的姿态测量系统，除了通常的滚动和俯仰测量之外，还需要持续更新，适度准确的偏航测量。连续偏航测量使得能够在存在扰动转矩的情况下控制航天器偏航轴。太阳传感器产生可用于校准由地球传感器和空对地链路产生的信号的组合导出的连续更新的偏航测量的信号。

88. 发明授权

US5080307A Spacecraft earth-pointing attitude acquisition method 失效
标题翻译：交通指标收购方法
公开(公告)号：US5080307A
公开(公告)日：1992-01-14
申请号：US522873
申请日：1990-05-14
申请人： John W. Smay , John F. Yocum , William F. Hummel
发明人： John W. Smay , John F. Yocum , William F. Hummel
IPC分类号： B64G1/24 , B64G1/36 , G01C1/00 , G01C21/24 , G05D1/08
CPC分类号： G05D1/0883 , B64G1/363 , B64G1/365 , B64G2001/245
摘要： A method for acquiring Earth-pointing attitude of a three-axis, body-stabilized spacecraft orbiting the Earth in a prescribed orbit plane, e.g. a geosynchronous communications satellite, including the steps of aligning the roll axis of the spacecraft with the sun line (which is the vector directed from the spacecraft to the Sun); then, orienting the spacecraft such that the angle formed between the yaw axis and the sun line is equal to the Earth-Sun angle (which is the angle formed between the sun line and a vector directed from the origin of the spacecraft internal coordinate system to the Earth); then, orienting the spacecraft such that the yaw axis is aligned with the center of the Earth; and finally, rotating the spacecraft about its yaw axis until its pitch axis is oriented at a desired attitude relative to the orbit plane, e.g., normal to the orbit plane, to thereby complete acquisition of the Earth-pointing attitude.

89. 发明授权

US5047945A Residual magnetic dipole cancellation system for satellites 失效
标题翻译：用于卫星的残余磁偶极子取消系统
公开(公告)号：US5047945A
公开(公告)日：1991-09-10
申请号：US564994
申请日：1990-08-09
申请人： Michael A. Paluszek
发明人： Michael A. Paluszek
IPC分类号： B64G1/28 , B64G1/32 , B64G1/36 , G05D1/08
CPC分类号： B64G1/32 , B64G1/283 , B64G1/285 , B64G1/36 , B64G1/363 , B64G1/365 , G05D1/0883
摘要： The magnitude and direction of the residual magnetic field or dipole of an orbiting spacecraft is estimated from the attitude-perturbing effects of its interaction with the magnetic field of the heavenly body about which it orbits. The measurements are performed over a significant portion of an orbit. The estimate uses h, the total spacecraft momentum in the body frame, and its body angular rate .omega.. The Earth's magnetic flux density B is determined either by magnetometer measurements, or by recourse to stored historical and ephemeris information.
摘要翻译：轨道航天器的残余磁场或偶极子的大小和方向根据其与轨道运行的天体的磁场的相互作用的姿态扰动效应估计。测量在轨道的很大部分进行。估计使用h，身体框架中的航天器总体动量及其身体角速度ω。地球的磁通密度B可以通过磁力计测量，或通过追求存储的历史和星历信息来确定。

90. 发明授权

US4723735A Energy storage attitude control and reference system 失效
标题翻译：储能姿态控制与参考系统
公开(公告)号：US4723735A
公开(公告)日：1988-02-09
申请号：US687068
申请日：1984-12-28
申请人： David B. Eisenhaure , James R. Downer , Tim E. Bliamptis , George A. Oberbeck , Susan D. Hendrie
发明人： David B. Eisenhaure , James R. Downer , Tim E. Bliamptis , George A. Oberbeck , Susan D. Hendrie
IPC分类号： B64G1/28 , B64G1/36 , G05D1/08 , H02J3/30 , H02K7/02
CPC分类号： F16C32/0444 , B64G1/283 , B64G1/285 , B64G1/288 , B64G1/36 , G05D1/0883 , H02J3/30 , H02K7/025 , B64G1/361 , B64G1/363 , Y02E60/16
摘要： An energy storage attitude control and reference system for a craft including at least two flywheels with their angular momenta balanced to produce zero net angular momentum and at least two motor/generator units each including one of the flywheels in its rotor structure. The system further includes one pair of bearings for supporting each of the flywheels, means for measuring the position of each flywheel relative to its bearings, means for resolving current to and from said motor/generator units, means for applying torques to each flywheel through its respective bearings for controlling attitude of the craft about two mutually perpendicular axes, and means for exerting torques to each flywheel through its respective motor/generator to provide attitude control of the craft about a third axis perpendicular to the first two and for controlling the energy storage level of the flywheels.
摘要翻译：一种用于飞行器的能量储存姿态控制和参考系统，其包括具有其角动量平衡的至少两个飞轮以产生零净角动量，以及至少两个马达/发电机单元，每个包括其转子结构中的一个飞轮。该系统还包括一对用于支撑每个飞轮的轴承，用于测量每个飞轮相对于其轴承的位置的装置，用于将电流分离到所述马达/发电机单元和从所述马达/发电机单元分离的装置，用于通过其飞轮向每个飞轮施加转矩的装置用于控制工作人员围绕两个相互垂直的轴线的姿态的相应的轴承，以及用于通过其相应的电动机/发电机向每个飞轮施加扭矩的装置，以提供围绕垂直于前两个的第三轴的飞行器的姿态控制，并且用于控制能量存储飞轮的水平。

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