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21. 发明公开

EP2204321A3 Method for improving maneuverability and controllability by simultaneously applying both reaction wheel-based attitude controller and thruster-based attitude controller 有权
标题翻译：一种用于改善由reaktionsradbasierter位置控制和位置控制基于推进器的同时应用的装置的可操作性和可控制性过程
公开(公告)号：EP2204321A3
公开(公告)日：2010-11-10
申请号：EP09172637.2
申请日：2009-10-09
申请人： Korea Aerospace Research Institute
发明人： Seo, Hyun Ho , Yong, Ki Lyuk , Oh, Shi Hwan , Choi, Hong Taek , Lee, Seon Ho , Yim, Jo Ryeong , Kim, Yong Bok , Lee, Hye Jin
IPC分类号： B64G1/26 , B64G1/28 , G05D1/08
CPC分类号： B64G1/26 , B64G1/283 , B64G2001/245 , G05D1/0883
摘要： Provided are an attitude control system (100) and method of a spacecraft of an artificial satellite that may enhance a maneuverability and a controllability by simultaneously applying a reaction wheel and a thruster among drive units used to maneuver an attitude of the spacecraft of the artificial satellite. The attitude control system may include: a thruster-based attitude controller (110) which control firing time of thrusters mounted on the spacecraft; and a reaction wheel-based attitude controller (120) controlling driving of a reaction wheel mounted on the spacecraft. The spacecraft may include a plurality of reaction wheels. When a defect occurs in the spacecraft due to a partial malfunction of the reaction wheels, an attitude maneuverability of the spacecraft may be corrected by simultaneously applying the thruster-based attitude controller and the reaction wheel-based attitude controller.

22. 发明公开

EP2022718A4 ATTITUDE CONTROL DATA CREATING METHOD, AND ATTITUDE CONTROL DEVICE APPLYING THE METHOD 有权
标题翻译：程序对产生位置控制数据和程序赋予装置进行位置控制
公开(公告)号：EP2022718A4
公开(公告)日：2010-07-07
申请号：EP07743244
申请日：2007-05-02
申请人： NEC TOSHIBA SPACE SYS LTD , JAPAN AEROSPACE EXPLORATION
发明人： KAMIYA TOSHIO , MAEDA KEN , HASHIMOTO TATSUAKI , SAKAI SHINICHIRO
IPC分类号： B64G1/24 , G05D1/08
CPC分类号： B64G1/24 , B64G1/283 , B64G1/286 , B64G1/36 , B64G1/38 , G05D1/0883

23. 发明公开

EP1807305A2 INTEGRATED MOMENTUM WALL 失效
标题翻译：具有集成PULSE WALL
公开(公告)号：EP1807305A2
公开(公告)日：2007-07-18
申请号：EP05857735.4
申请日：2005-11-02
申请人： Honeywell International, Inc.
发明人： JACOBS, Jack, H.
IPC分类号： B64G1/28 , G05D1/08
CPC分类号： B64G1/283 , B64G1/286 , B64G1/425 , B64G1/426 , B64G1/428 , H02K7/02 , Y02E60/16
摘要： A vehicle control system (200) is provided that includes a slat (206) having an axis, a plurality of microwheels (204) disposed on the slat (206), each microwheel (204) having a first stator wafer (208), a second stator wafer (210), and a rotor wafer (212) disposed therebetween, the first and second stator wafers (208, 210) configured to spin the rotor wafer (212), and an actuator (104) coupled to the slat (206) and configured to at least partially rotate the slat (206) about the axis.

24. 发明授权

EP1391383B1 System and method for reducing mechanical disturbances from energy storage flywheels 失效
标题翻译：方法和系统减少储能飞轮机械扰动
公开(公告)号：EP1391383B1
公开(公告)日：2006-05-24
申请号：EP03022223.6
申请日：1997-11-27
申请人： NORTHROP GRUMMAN CORPORATION
发明人： Spector, Victor A.
IPC分类号： B64G1/28 , B64G1/42
CPC分类号： B64G1/426 , B64G1/28 , B64G1/283 , B64G1/42 , B64G1/428

25. 发明授权

EP1110862B1 Combined roll-yaw spacecraft steering method for low earth orbit target trajectory compensation 有权
标题翻译：用于平衡低轨道组合滚偏航航天器的控制方法
公开(公告)号：EP1110862B1
公开(公告)日：2004-03-10
申请号：EP00127669.0
申请日：2000-12-18
申请人： The Boeing Company
发明人： Villani, Daniel D. , Rosen, Harold A.
IPC分类号： B64G1/24 , H04B7/195 , G05D1/08 , H01Q1/28 , H01Q3/08
CPC分类号： B64G1/24 , B64G1/242 , B64G1/26 , B64G1/283 , B64G1/36 , B64G1/363 , B64G1/365 , B64G1/66

26. 发明公开

EP1065516A3 Ephemeris/attitude reference determination using on-board optics and other satellite ephemeris 审中-公开
标题翻译：参考星历和通过光学部件的位置确定和夹带的星历从其它卫星
公开(公告)号：EP1065516A3
公开(公告)日：2004-02-18
申请号：EP00111942.9
申请日：2000-06-15
申请人： Northrop Grumman Corporation
发明人： Wehner, James W.
IPC分类号： G01S5/16 , G01S5/02 , B64G1/24 , B64G1/36
CPC分类号： H04B10/118 , B64G1/1007 , B64G1/242 , B64G1/26 , B64G1/28 , B64G1/283 , B64G1/288 , B64G1/32 , B64G1/36 , B64G1/66 , B64G3/00 , B64G2001/245 , G05D1/0883
摘要： The present invention provides a system (200) for determining the ephemeris and attitude for a spacecraft based on optical payload pointing directions and the ephemeris of other spacecraft. An ephemeris determining subsystem (300) obtains ephemeris data (308) for one or more reference spacecraft. Optical payload pointing information (306) is obtained for the optical payload pointed to the reference spacecraft. The spacecraft ephemeris (312) is then calculated with ephemeris determination algorithms (302) based on the ephemeris data (308) and optical payload pointing information (306). Other available information, such as stored results of previous measurements and calculations, time (310), spacecraft attitude (304), information from non-payload sensors and ranging information may be used to enhance the accuracy or decrease the complexity of the ephemeris calculations. In addition to ephemeris determination, the present invention also provides an attitude determining subsystem (800) for the determination of spacecraft attitude (810). Ephemeris data for reference spacecraft (806) and optical payload pointing information (802) is obtained. The spacecraft attitude is then calculated by attitude determination algorithms (804) based on the ephemeris of reference spacecraft (806) pointed to by the optical payload and the optical payload pointing information (802). Other available information, such as stored results of previous measurements and calculations, time (808), information from non-payload sensors, and ranging information may be used to enhance the accuracy or decrease the complexity of the attitude calculations.

27. 发明授权

EP1107852B1 MOMENT CONTROL UNIT FOR SPACECRAFT ATTITUDE CONTROL 有权
标题翻译：涡流控制单元适用于空间飞行器位置控制
公开(公告)号：EP1107852B1
公开(公告)日：2004-01-14
申请号：EP99960101.6
申请日：1999-08-05
申请人： Honeywell Inc.
发明人： DAVIS, Lawrence, P. , HYDE, Tristam, T.
IPC分类号： B64G1/28 , G05D1/08
CPC分类号： B64G1/286 , B64G1/283 , B64G1/285 , B64G1/36 , G05D1/0883
摘要： A moment control device (120) for positioning a spacecraft which employs a plurality of spinning bodies (122, 124, 126, 128) operable to impart a desired torque to a space craft, the bodies being constructed in a unitary combination and the unitary combination being mounted to the spacecraft to be positioned.

28. 发明授权

EP1095852B1 Système de gestion d'énergie électrique et de contrôle d'attitude pour satellite 有权
标题翻译：对于卫星的位置和功率控制系统
公开(公告)号：EP1095852B1
公开(公告)日：2003-11-26
申请号：EP00402980.7
申请日：2000-10-26
申请人： Astrium SAS
发明人： Barde, Henri
IPC分类号： B64G1/28 , B64G1/42 , H02J3/30 , G05D1/08
CPC分类号： B64G1/426 , B64G1/283 , B64G1/428 , G05D1/0883

29. 发明公开

EP1092626A3 Solar wing thermal shock compensation using solar wing position actuator 有权
标题翻译：在施加其致动器上的太阳能翼热冲击的补偿
公开(公告)号：EP1092626A3
公开(公告)日：2002-09-25
申请号：EP00121358.6
申请日：2000-10-11
申请人： Hughes Electronics Corporation
发明人： Liu, Ketao
IPC分类号： B64G1/44 , B64G1/24
CPC分类号： B64G1/407 , B64G1/24 , B64G1/283 , B64G1/288 , B64G1/361 , B64G1/363 , B64G1/366 , B64G1/38 , B64G1/443
摘要： A method, apparatus, article of manufacture for compensating for solar wing thermal shock in a spacecraft (100) is disclosed. The method comprises the steps of determining solar wing compensation to compensate for the thermal shock disturbance and rotating the solar wing (114) about a second axis (110) according to the determined compensation, wherein the second axis (110) is substantially perpendicular to a first axis (118) and to a vector (204) from the spacecraft (100) to the sun. The solar wing compensation can be based on predicted solar wing (114) deflections due to thermal shock perturbations, or if available, solar wing temperature measurements. In an embodiment of the present invention applicable to satellites with multiple solar wings (114), asymmetric control is applied by independent adjustment of the thermal shock compensation loop (302) controlling each solar wing (114). In yet another embodiment of the present invention, the solar wing position actuator (108) is further commanded by a feedback control loop (330) using the measured spacecraft attitude. The apparatus comprises an attitude control system having a device (310) for predicting or measuring solar wing perturbations, at least one solar wing position actuator (108), cooperatively coupled to the solar wing (114) for rotating the solar wing (114) about a second axis (110), wherein the second axis (110) is substantially perpendicular to the first axis (108) and to a vector (204) from the spacecraft (100) to the sun, and a thermal shock compensation loop (302), for generating at least one solar wing position actuator command (316) to rotate the solar wing (114) about the second axis (110) in accordance with the predicted or measured solar wing perturbations.

30. 发明公开

EP1093041A3 Verfahren zur Lageregelung und Stabilisierung eines Raumfahrzeuges 失效
标题翻译：航天器姿态控制和稳定的方法
公开(公告)号：EP1093041A3
公开(公告)日：2001-05-16
申请号：EP00125878.9
申请日：1996-08-12
申请人： Astrium GmbH
发明人： Surauer, Michael , Keeve, Rolf , Ertongur, Nahit
IPC分类号： G05D1/08
CPC分类号： B64G1/361 , B64G1/24 , B64G1/26 , B64G1/28 , B64G1/281 , B64G1/283 , B64G1/285 , B64G1/288 , B64G1/32 , B64G1/363 , B64G1/365 , B64G2001/245 , G05D1/0883
摘要： Die Erfindung betrifft eine Vorrichtung zur Lageregelung und Stabilisierung eines dreiachsenstabilisierten, drallbehafteten Raumfahrzeuges sowie entsprechende Verfahren. Das Raumfahrzeug ist mit einer Drallradanordnung, die einen Drehimpulsvektor vorzugsweise in Richtung der Nickachse sowie Regelmomente um alle drei Hauptachsen unabhängig voneinander erzeugen kann, ausgestattet. Ferner besitzt es einen Lageabweichungen um eine erste Querachse, vorzugsweise die Rollachse, messenden Lagesensor sowie Aktuatoren zur Erzeugung äußerer Regelmomente. Es ist ein Entkopplungs-regler vorgesehen, welcher ein einseitig die Entkopplung der Rolldynamik von der Gierdynamik bewirkendes Stellsignal für die Drallradanordnung bildet. Weiterhin ist zur Schätzung der Lageabweichung um eine zweite Querachse, vorzugsweise die Gierachse, ein reduzierter Beobachter zweiter Ordnung vorhanden, welcher die Übertragungsfunktion des geschlossenen Regelkreises für die erste Querachse berücksichtigt. Für den Fall von Lagemessungen um beide Querachsen ist ein Verfahren zur Erzeugung von Regelmomenten um diese Achsen mittels der Drallradanordnung sowie der Aktuatoren angegeben. Für den Fall des Verlustes einer Querachsenreferenz ist ein Verfahren unter Verwendung eines Beobachters angegeben, welchem geschätzte Störmomente zugeführt werden.
摘要翻译：本发明涉及一种用于三轴稳定旋涡航天器的位置控制和稳定的装置以及相应的方法。该宇宙飞船配备有涡旋轮装置，其可以优选地在俯仰轴的方向上产生角动量矢量，并且独立于彼此地围绕所有三个主轴线控制力矩。此外，它具有关于第一横向轴线的位置偏差，最好是侧倾轴线，测量位置传感器和用于产生外部控制力矩的致动器。提供了一个去耦合调节器，该去耦调节器形成导致旋转轮组件的控制信号的偏航动态的滚动动态的单侧解耦。此外，为了估计关于第二横向轴线，优选偏航轴线的位置偏差，存在减小的二阶观察器，其考虑了用于第一横向轴线的闭合控制回路的传递函数。在关于两个横向轴线的位置测量的情况下，规定了通过涡流轮装置和致动器产生关于这些轴线的控制力矩的方法。在交叉轴参考丢失的情况下，指示使用施加了估计的扰动转矩的观测器的方法。

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