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51. 发明授权

US5054719A Active three-axis attitude control system for a geostationary satellite 失效
标题翻译：用于地球卫星的主动三轴姿态控制系统
公开(公告)号：US5054719A
公开(公告)日：1991-10-08
申请号：US417759
申请日：1989-10-05
申请人： P. A. Alexandre Maute
发明人： P. A. Alexandre Maute
IPC分类号： B64G1/28 , B64G1/24 , B64G1/36 , G05D1/08 , G09B9/52
CPC分类号： B64G1/36 , B64G1/24 , G05D1/0883 , G09B9/52 , B64G1/288 , B64G1/361 , B64G1/363 , B64G1/365
摘要： An attitude control system for a stabilized geostationary satellite comprising at least one terrestrial detector (T.sub.1) and a stellar detector oriented towards the North further comprises:a processing subsystem for each of at least the normal mode (I) and the stationkeeping mode (II), adapted to be connected to the detectors and to actuators (11, 12, 13) and comprising a pre-processing module (14-16) adapted to determine for each axis i an angular offset .epsilon..sub.i between a measured angle determined from the detectors and a reference angle together with a control and correction module (18, 20) adapted to determine for each axis a corrective torque of the form:c=k.sub.i..epsilon..sub.i +h.sub.i..epsilon..sub.iwhere k.sub.i and h.sub.i are parameters specific to each axis and to each processing line,a speed .epsilon..sub.i measuring unit (24,25),and a mode selection unit (26) connecting the detectors to a selected processing line and that processing line to at least one actuator.
摘要翻译：一种用于稳定地球静止卫星的姿态控制系统，包括至少一个地面探测器（T1）和朝向北方的恒星探测器，进一步包括：用于至少正常模式（I）和驻留模式（II）中的每一个的处理子系统，，适于连接到检测器和致动器（11,12,13），并且包括预处理模块（14-16），其适于为每个轴线i确定从检测器确定的测量角度之间的角度偏移εi 以及与控制和校正模块（18,20）一起的参考角，其适于为每个轴确定以下形式的校正扭矩：c = ki。 epsilon i +嗨其中ki和hi是每个轴和每个处理线特有的参数，速度ε测量单元（24,25）和将检测器连接到选定的处理线的模式选择单元（26），并且该处理线至少一个致动器。

52. 发明授权

US4848706A Spacecraft attitude control using coupled thrusters 失效
标题翻译：使用耦合推进器的航天器姿态控制
公开(公告)号：US4848706A
公开(公告)日：1989-07-18
申请号：US161931
申请日：1988-02-29
申请人： Subhash C. Garg , Mahabaleshwar K. P. Bhat
发明人： Subhash C. Garg , Mahabaleshwar K. P. Bhat
IPC分类号： B64G1/26 , G05D1/08 , G09B9/52
CPC分类号： G09B9/52 , B64G1/26 , G05D1/0883
摘要： An attitude control system for a three-axis controlled spacecraft (1) in which the location of thrusters causes significant cross-coupling torques. A thruster command conditioning electronics module (TCCEM) (3) is positioned between the conventional roll, pitch, and yaw loop controllers (41-43) and the thrusters (61-63). The TCCEM (3) converts spacecraft-axis-based torque requirement signals (TDX, TDY, TDZ) emanating from the loop controllers (41-43) into scalar quantities (UL, UM, UN) that are input to thruster modulators (51-53) that turn on one or more thrusters of the thruster pairs (L,M,N). The TCCEM (3) causes the spacecraft (1) attitude to be adjusted as commanded by the torque requirement signals (TDX, TDY TDZ) despite the presence of the cross-coupling. Two embodiments are illustrated: a working embodiment in which cross-coupling torques are produced about two axes (Y,Z), and a more general embodiment in which cross-coupling torques are present about all three axes (X,Y,Z).

53. 发明授权

US4776540A Method of orienting a synchronous satellite 失效
标题翻译：定向同步卫星的方法
公开(公告)号：US4776540A
公开(公告)日：1988-10-11
申请号：US133249
申请日：1987-12-10
申请人： Lawrence H. Westerlund
发明人： Lawrence H. Westerlund
IPC分类号： B64G1/24 , B64G1/28 , B64G1/34 , B65D5/42 , B65D5/52 , G05D1/08 , G09B9/52
CPC分类号： B65D5/4208 , B64G1/24 , B64G1/281 , B65D5/52 , G05D1/0883 , G09B9/52 , B64G1/285 , B64G1/34
摘要： The invention is a method of orienting a satellite in a geosynchronous orbit so as to direct a beam from an antenna mounted on the satellite to cover a desired target site, and pointing the beam axis at a desired bore site target. One embodiment of the method according to the invention includes a step of orienting the spin axis of a geosynchronous satellite at a direction angle which equals the inclination angle of the current orbital plane plus an adjustment or correction angle (.beta.), when the inclination angle is greater than zero. The correction angle is determined using one or both of the following equations:.beta.=BS-tan.sup.-1 {[ sin (bs-I)]/[6.61-cos (bs-I)]},or.beta.=.vertline.-(BS-tan.sup.-1 {[ sin (bs+I)]/[6.61-cos (bs+I)]}).vertline.,where, BS=the elevation angle of the bore site target in spacecraft coordinates, bs=the latitude of the bore site target, I=the inclination angle of the orbital plane with respect to the equatorial plane, and .beta.=the correction angle with respect to orbit-normal to point the axis of the beam at the desired bore site target. The step of orienting the satellite at the direction angle is performed by using thrusters. A magnetic torquing system could also be used.
摘要翻译：本发明是将卫星定向在地球同步轨道中的方法，以便将来自安装在卫星上的天线的波束引导到覆盖期望的目标地点，并将波束轴指向所需的孔位点目标。根据本发明的方法的一个实施例包括以下步骤：当倾斜角度为倾斜角度时，将地球同步卫星的旋转轴定向在等于当前轨道平面的倾斜角加上调整或校正角度（β）的方向角度大于零。使用以下等式中的一个或两个来确定校正角度：β= BS-tan-1 {[sin（bs-1）] / [6.61-cos（bs-1）]}或β= | - （BS -an-1 {[sin（bs + I）] / [6.61-cos（bs + I）]}）|，其中，BS =航天器坐标中孔径目标的仰角，bs = 钻孔位置目标I =轨道平面相对于赤道平面的倾斜角度，β=相对于轨道法线的修正角度，以将梁的轴线指向所需孔径目标点。通过使用推进器来执行卫星在方位角定向的步骤。也可以使用磁力扭矩系统。

54. 发明授权

US4746976A Star sightings by satellite for image navigation 失效
标题翻译：通过卫星进行星形瞄准用于图像导航
公开(公告)号：US4746976A
公开(公告)日：1988-05-24
申请号：US867356
申请日：1986-05-23
申请人： Ahmed A. Kamel , Donald E. Ekman , John Savides , Gerald J. Zwirn
发明人： Ahmed A. Kamel , Donald E. Ekman , John Savides , Gerald J. Zwirn
IPC分类号： B64G1/36 , G01C21/02 , G01C21/24 , G06T1/00 , G09B9/52 , H04N7/18
CPC分类号： G01C21/025 , G09B9/52
摘要： Stars are sensed by one or more instruments (1, 2) on board a three-axis stabilized satellite, for purposes of assisting in image navigation. A star acquistion computer (64), which may be located on the earth, commands the instrument mirror (33, 32) to slew just outside the limb of the earth or other celestial body around which the satellite is orbiting, to look for stars that have been cataloged in a star map stored within the computer (64). The instrument (1, 2) is commanded to dwell for a period of time equal to a star search window time, plus the maximum time the instrument (1, 2) takes to complete a current scan, plus the maximum time it takes for the mirror (33, 32) to slew to the star. When the satellite is first placed in orbit, and following first stationkeeping and eclipse, a special operation is performed in which the star-seeking instrument (1, 2) FOV is broadened. The elevation dimension can be broadened by performing repetitive star seeks; the azimuth dimension can be broadened by lengthening the commanded dwell times.
摘要翻译：星星由一个或多个仪器（1,2）感测在三轴稳定的卫星上，目的是协助图像导航。可以位于地球上的星形采集计算机（64）命令仪器镜（33,32）正好在卫星绕轨道的地球或其他天体的肢体外面去寻找恒星已经在存储在计算机内的星图中编目了（64）。命令仪器（1,2）驻留一段时间等于星形搜索窗口时间，加上仪器（1,2）完成当前扫描所需的最长时间，加上最长时间镜子（33,32）转向星星。当卫星首次放置在轨道上，并且在第一次保存和日食之后，执行寻星仪器（1,2）FOV的特殊操作。通过执行重复的星际搜索可以扩大海拔尺寸; 通过延长指令停留时间可以扩大方位角尺寸。

55. 发明授权

US2687582A Astronomy and celestial navigation teaching device 失效
标题翻译：天文与天文导航教学装置
公开(公告)号：US2687582A
公开(公告)日：1954-08-31
申请号：US30008352
申请日：1952-07-21
申请人： STORZ LEON A
发明人： STORZ LEON A
IPC分类号： G09B9/52
CPC分类号： G09B9/52

56. 发明授权

US2420048A Training device 失效
公开(公告)号：US2420048A
公开(公告)日：1947-05-06
申请号：US48033043
申请日：1943-03-24
申请人： LINK AVIATION INC
发明人： MARSH HAROLD A
IPC分类号： G09B9/52
CPC分类号： G09B9/52

57. 发明授权

EP2929520B1 MOTION CONTROL APPARATUS 有权
标题翻译：运动控制装置
公开(公告)号：EP2929520B1
公开(公告)日：2018-03-14
申请号：EP13805486.1
申请日：2013-12-06
申请人： Williams Grand Prix Engineering Limited
发明人： KIRKMAN, David
IPC分类号： G09B9/04 , G09B9/12
CPC分类号： G09B9/12 , G09B9/04 , G09B9/06 , G09B9/52
摘要： A motion simulator (10) has a body tub (12) fixed on a carrier platform (14), the carrier platform being supported via motion control apparatus (52, 54, 56, 58), each having bearings which translate along an inclined path, the motion control apparatuses together providing six degrees of motion for the carrier platform.

58. 发明授权

EP0618541B1 Interactive graphics computer system for planning star-sensor-based satellite attitude maneuvers 失效
标题翻译：基于星探测器数据规划卫星姿态变更操纵交互式图形计算机系统
公开(公告)号：EP0618541B1
公开(公告)日：2003-03-12
申请号：EP94103886.1
申请日：1994-03-14
申请人： International Business Machines Corporation
发明人： Pritt, Mark D. , Greening, Thomas B.
IPC分类号： G01C21/24 , B64G1/36 , G09B9/08
CPC分类号： B64G1/361 , B64G1/22 , B64G1/24 , G01C21/24 , G01S3/7867 , G09B9/52 , Y10S715/973

59. 发明授权

EP0247265B1 Star sightings by satellite for image navigation 失效
标题翻译：由卫星导航恒星位置确定装置，用于图像的参考点。
公开(公告)号：EP0247265B1
公开(公告)日：1994-03-09
申请号：EP86309782.0
申请日：1986-12-15
申请人： SPACE SYSTEMS / LORAL INC.
发明人： Kamel, Ahmed A. , Ekman, Donald E. , Savides, John , Zwirn, Gerald
IPC分类号： G01C21/00
CPC分类号： G01C21/025 , G09B9/52

60. 发明公开

EP0334485A2 Spacecraft attitude control using coupled thrusters 失效
标题翻译： Lageregelung eines Raumfahrzeuges mit gekoppeltenSchubdüsen。
公开(公告)号：EP0334485A2
公开(公告)日：1989-09-27
申请号：EP89301621.2
申请日：1989-02-20
申请人： SPACE SYSTEMS / LORAL INC.
发明人： Garg, Subhash C. , Bhat,Mahabaleshwar K. P.
IPC分类号： G05D1/08 , B64G1/26
CPC分类号： G09B9/52 , B64G1/26 , G05D1/0883
摘要： An attitude control system for a three-axis controlled spacecraft (1) in which the location of thrusters causes significant cross-coupling torques. A thruster command conditioning electronics module (TCCEM) (3) is positioned between the conventional roll, pitch, and yaw loop controllers (41-43) and the thrusters (61-63). The TCCEM (3) converts spacecraft-axis-based torque requirement signals (TDX, TDY, TDZ) emanating from the loop controllers (41-43) into scalar quantities (UL, UM, UN) that are input to thruster modulators (51-53) that turn on one or more thrusters of the thruster pairs (L,M,N). The TCCEM (3) causes the spacecraft (1) attitude to be adjusted as commanded by the torque requirement signals (TDX, TDY, TDZ) despite the presence of the cross-coupling. Two embodiments are illustrated: a working embodiment in which cross-coupling torques are produced about two axes (Y,Z), and a more general embodiment in which cross-coupling torques are present about all three axes (X,Y,Z).
摘要翻译：一种用于三轴控制航空器（1）的姿态控制系统，其中推进器的位置导致显着的交叉耦合扭矩。推进器命令调节电子模块（TCCEM）（3）位于传统的滚动，俯仰和偏航环路控制器（41-43）和推进器（61-63）之间。 TCCEM（3）将从循环控制器（41-43）发出的基于航空器的轴的扭矩要求信号（TDX，TDY，TDZ）转换成标量（UL，UM，UN），输入到推进器调制器（L，M，N）的推进器的一个或多个推进器。尽管存在交叉耦合，TCCEM（3）使得航天器（1）的姿态被扭矩要求信号（TDX，TDY，TDZ）所指示。示出了两个实施例：围绕两个轴线（Y，Z）产生交叉耦合转矩的工作实施例以及其中围绕所有三个轴线（X，Y，Z）存在交叉耦合转矩的更一般实施例。

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