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1. 发明公开

EP3144229A4 SPHERE MAGNETIC LEVITATION SYSTEM AND METHOD OF OPERATING SPHERE MAGNETIC LEVITATION SYSTEM 有权
公开(公告)号：EP3144229A4
公开(公告)日：2018-01-17
申请号：EP14891649
申请日：2014-08-19
申请人： KOREA AEROSPACE RES INSTITUTE
发明人： LEE SEON HO
IPC分类号： H02N15/00 , B64G1/28
CPC分类号： G09B9/52 , B64G1/28 , B64G7/00 , G01M99/00 , H02K7/09 , H02N15/00
摘要： The present invention introduces a sphere magnetic levitation system having magnetic aligning devices that magnetically align the position of a sphere levitated by electromagnets provided on the periphery of the sphere according to whether the sphere is levitated, and a method of operating the sphere magnetic levitation system. The sphere magnetic levitation system includes: a sphere; a plurality of electromagnets symmetrically positioned about the sphere and spaced apart from the sphere at equal distances; and a plurality of magnetic-aligning devices provided around the sphere, and coming into contact with the sphere or separated from the sphere by a predetermined distance according to the modes of the sphere magnetic levitation system. The system is operated in one mode from among: an idle mode, in which the magnetic-aligning devices are in direct contact with and support the sphere; and an operation mode, in which the magnetic-aligning devices are separated from the sphere and the sphere is levitated and rotated.

2. 发明公开

EP2955114A4 CONTROL MOMENT GYROSCOPE 有权
标题翻译：镇定SCHWUNGRAD
公开(公告)号：EP2955114A4
公开(公告)日：2016-12-14
申请号：EP13879953
申请日：2013-10-25
申请人： KOREA AEROSPACE RES INST
发明人： LEE SEON HO
IPC分类号： B64G1/28 , G01C19/04 , G05D1/08
CPC分类号： G01C19/30 , B64G1/28 , B64G1/286 , F16F15/30
摘要： The objective of the present invention is to provide a control moment gyroscope which can be provided in a limited space since the volume thereof can be reduced without a change in performance by optimizing the shapes and mounting positions of each component. To this end, the control moment gyroscope of the present invention is a control moment gyroscope for generating torque in the orthogonal directions to both of two shafts which are perpendicularly disposed to each other by rotating the two shafts, and the control moment gyroscope comprises: a gimbal motor formed in the shape of a hollow cylinder and supplying momentum; spin motor provided in the inside of the gimbal motor and supplying momentum in a perpendicular direction to the momentum of the gimbal motor; and a flywheel provided in the inside of the gimbal motor and supplied with the rotational force of the gimbal motor and the rotational force of the spin motor.

3. 发明公开

EP2758311A1 PROCEDE DE CONTROLE D'ATTITUDE D'UN SATELLITE ET SATELLITE COMMANDE EN ATTITUDE 有权转让
标题翻译：法中卫星的位置控制和位置控制的卫星
公开(公告)号：EP2758311A1
公开(公告)日：2014-07-30
申请号：EP12759743.3
申请日：2012-09-19
申请人： Astrium SAS
发明人： POLLE, Bernard
IPC分类号： B64G1/26 , B64G1/28 , B64G1/40
CPC分类号： B64G1/28 , B64G1/242 , B64G1/26 , B64G1/283 , B64G1/407 , B64G1/443 , B64G2001/245
摘要： The present invention concerns a method of controlling the attitude of a satellite in orbit around a celestial body, the attitude of the satellite being controlled by means of a momentum storage device and by means of controllable surfaces of the satellite capable of creating desaturation torques in the storage device by using solar pressure, said controllable surfaces being arranged on solar panels mobile in rotation around an axis Y. The attitude of the satellite is also controlled by means of at least one electric thruster also implemented to control the orbit of the satellite, the orientation of the at least one electric thruster being controlled in such a way as to activate said at least one electric thruster with a thrust direction deliberately not aligned with a centre of mass of the satellite in order to create desaturation torques in the storage device along axis Y, the controllable surfaces being controlled to create desaturation torques of said storage device in a plane orthogonal to the Y axis. The present invention also concerns an attitude-controlled satellite (10).

4. 发明授权

EP1680648B1 CONTROLE D'ATTITUDE DE SATELLITES EN PARTICULIER AGILES A NOMBRE REDUIT DE GYRODYNES 有权
标题翻译：用于控制卫星的位置，特别是与控制力矩陀螺卫星敏捷数量减少
公开(公告)号：EP1680648B1
公开(公告)日：2012-07-25
申请号：EP04805353.2
申请日：2004-10-29
申请人： EADS ASTRIUM SAS
发明人： DEFENDINI, Ange , GHEZAL, Mehdi
IPC分类号： G01C19/00 , B64G1/28 , G05D1/08
CPC分类号： G05D1/0883 , B64G1/26 , B64G1/28 , B64G1/286 , B64G1/32
摘要： The invention relates to a method of controlling the attitude of a satellite (1) comprising two gyrodynes (3, 4) and a third main actuator (2) which delivers torques at least along the Z axis. The inventive method consists in: fixing the gimbal axes, A1 and A2, of the gyrodynes (3, 4) parallel to Z; setting a non-zero bias (e) between the angular momentum vectors (Formula I) of the gyrodynes; using the measurements provided by the sensors on board the satellite to estimate the kinematic and dynamic variables necessary in order to control the attitude of the satellite (1); calculating set variables in order to realise the objectives assigned to the satellite (1) attitude control system; and using the deviations between the estimated variables and the set variables to calculate control orders and to send same to the main actuators (2, 3, 4) in order to control the changing deviations over time, the control orders transmitted to the gyrodynes (3, 4) comprising orders which are used to vary the orientation of the gimbal axis thereof.

5. 发明公开

EP2181923A1 Procédé et système de désaturation des roues d'inertie d'un engin spatial 有权
标题翻译： Entsättigungsverfahrenund-systemfürdieTrägheitsrädereines Raumschiffs
公开(公告)号：EP2181923A1
公开(公告)日：2010-05-05
申请号：EP09169255.8
申请日：2009-09-02
申请人： Thales
发明人： Guyot, François
IPC分类号： B64G1/28
CPC分类号： B64G1/28 , B64G1/283
摘要： Le procédé de désaturation des roues d'inertie d'un engin spatial comportant trois axes de référence X, Y, Z, l'axe Z correspondant à une direction de pointage, consiste à renverser le sens d'accumulation du moment cinétique dans les roues par basculement automatique de l'engin spatial en rotation autour de l'axe Z, la direction de pointage restant fixe.
Application au domaine des satellites ou des sondes interplanétaires.
摘要翻译：该方法涉及通过使航天器围绕第一参考轴线自动倾斜以沿着第二参考轴，第三参考轴和第一参考轴卸载航天器来反转航天器的惯性轮中的动力矩的累积方向。第一参考轴对应于保持固定的指向方向，并且航天器以预定角度以旋转方式倾斜。还包括用于卸载航天器惯性轮的系统的独立权利要求。

6. 发明公开

EP1977972A1 Active control of soft hybrid isolation systems 有权
标题翻译： on hen we hen hen hen。。。。。。
公开(公告)号：EP1977972A1
公开(公告)日：2008-10-08
申请号：EP08101189.2
申请日：2008-01-31
申请人： Honeywell International Inc.
发明人： Hindle, Timothy A. , Hamilton, Brian J. , Jackson, Louis R.
IPC分类号： B64G1/64 , B64G1/26 , B64G1/28 , B64G1/36 , B64G1/32 , B64G1/40
CPC分类号： B64G1/641 , B64G1/26 , B64G1/28 , B64G1/283 , B64G1/286 , B64G1/32 , B64G1/36 , B64G1/407
摘要： Apparatus, Systems, and Methods are provided for controlling motion of a spacecraft (100). One apparatus includes a non-contacting actuator (3210) and a passive mechanical system (310) coupled in parallel with one another. A system includes a payload (110), a bus (120), and a hybrid actuator (300) including a non-contacting actuator and a passive mechanical system coupled in parallel, and coupled between the bus and the payload. The system also includes an inertial actuator (1210) configured to maneuver the bus to maintain a relative position and/or attitude of the bus with respect to the payload. One method includes receiving a signal instructing a first controller (2320) to change the position and/or attitude of a payload and utilizing a hybrid system to change the position and/or attitude of the payload. The method also includes receiving the signal at a second controller (2205) and utilizing a system to change a position and/or attitude of the bus independent of the payload.
摘要翻译：提供装置，系统和方法来控制航天器（100）的运动。一种装置包括彼此并联连接的非接触致动器（3210）和无源机械系统（310）。系统包括负载（110），总线（120）和混合致动器（300），其包括并联耦合的非接触致动器和无源机械系统，并且耦合在总线和有效载荷之间。该系统还包括惯性致动器（1210），其被配置为操纵总线以保持总线相对于有效载荷的相对位置和/或姿态。一种方法包括接收指示第一控制器（2320）改变有效载荷的位置和/或姿态并利用混合系统来改变有效载荷的位置和/或姿态的信号。该方法还包括在第二控制器（2205）处接收信号，并且利用系统来独立于有效载荷来改变总线的位置和/或姿态。

7. 发明授权

EP1134640B1 Attitude control system for a spacecraft 有权
标题翻译：对于空间飞行器位置控制
公开(公告)号：EP1134640B1
公开(公告)日：2007-11-07
申请号：EP00309213.7
申请日：2000-10-19
申请人： EADS Astrium Limited
发明人： Holt, Antony Philip
IPC分类号： G05D1/08 , B64G1/24
CPC分类号： B64G1/283 , B64G1/28 , B64G1/36 , B64G1/361 , B64G1/363 , G05D1/0883

8. 发明授权

EP1391384B1 System and method for reducing mechanical disturbances from energy storage flywheels 失效
标题翻译：方法和系统减少机械储能飞轮
公开(公告)号：EP1391384B1
公开(公告)日：2006-05-24
申请号：EP03022224.4
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

9. 发明公开

EP1484247A1 Actionneur gyroscopique, notamment pour dispositif de pilotage de l'attitude d'un satellite 有权
标题翻译： Gyroskopischer Stellantrieb，insbesonderefürdie Lageregelung eines Satelliten
公开(公告)号：EP1484247A1
公开(公告)日：2004-12-08
申请号：EP04076876.4
申请日：1999-07-21
申请人： EADS ASTRIUM SAS
发明人： Defendini, Ange , Lagadec, Kristen
IPC分类号： B64G1/28 , G01C19/06 , G01C19/08
CPC分类号： B64G1/28 , B64G1/283 , B64G1/286 , B64G2001/245 , G01C19/08 , G05D1/0883
摘要： L'actionneur gyroscopique comprend un support monté sur une embase (110) par des moyens permettant de le faire tourner autour d'un premier axe (120). Le support porte une toupie (134) par l'intermédiaire de moyens permettant de l'entraîner en rotation à vitesse élevée autour d'un second axe (132) orthogonal au premier. La toupie (134) comprend deux flasques (136) reliés par un arbre de diamètre très inférieur au diamètre des flasques et le support comprend des moyens sur lesquels tourne l'arbre.
摘要翻译：激活器具有安装在基座（110）上的支撑件（116）并通过直流扭矩马达（124）围绕轴线（120）旋转。支撑件保持旋转器（134），所述旋转器围绕垂直于轴线（120）的轴线（132）旋转，由转矩电动机（144）旋转。旋转器具有通过直径小于凸缘直径的轴（142）连接的两个凸缘（136）。支撑件具有轴（122），轴转动在其上。

10. 发明公开

EP1099093A1 SYSTEM AND METHOD FOR SPACECRAFT ATTITUDE CONTROL 审中-公开
标题翻译：系统空间飞行器位置控制
公开(公告)号：EP1099093A1
公开(公告)日：2001-05-16
申请号：EP99934422.9
申请日：1999-07-23
申请人： Bristol Aerospace Limited
发明人： STALEY, Douglas, A. , TYC, George , FRISE, Peter, R.
IPC分类号： G01C19/22 , B64G1/38 , F16C11/12
CPC分类号： B64G1/285 , B64G1/28 , B64G1/283 , B64G1/286 , B64G1/32 , B64G1/36 , F16D3/56 , F16D3/72
摘要： A momentum management system (10) for spacecraft attitude control. The momentum management system (10) includes a rotor (14) that provides control torques to a spacecraft. A drive (25) is provided to rotate the rotor (14), and a torque generation device (27) to impart torque to the rotor (14). A gimbal assembly (12) couples the drive (25) to the rotor (14). The gimbal assembly (12) has a spinning gimbal (18), and attaches to the drive (25) and the rotor (14) through the use of flexure joints (20). These flexure joints (20) permit the rotor (14) to tilt in two axes relative to a drive shaft (22), through a range of angles from about 0 degrees to about 7 degrees under the control of the torque generation device (27).

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