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41. 发明公开

EP0739818A1 Satellite spin axis stabilization using a single degree of freedom transverse momentum storage device 失效
标题翻译：在其中的横向Tägheitsmoment与自由的单一度被存储卫星自旋稳定方法，和系统，以
公开(公告)号：EP0739818A1
公开(公告)日：1996-10-30
申请号：EP96106080.3
申请日：1996-04-18
申请人： Hughes Aircraft Company
发明人： Fowell, Richard A. , Yocum, John F.
IPC分类号： B64G1/38 , B64G1/28 , G05D1/08
CPC分类号： B64G1/24 , B64G1/281 , B64G1/283 , B64G1/285 , B64G1/286 , B64G1/288 , B64G1/36 , B64G1/361 , B64G1/363 , B64G1/365 , B64G1/38 , G05D1/0883
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 (20), 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 (20), ensure tumble recover to a preferred orientation, and stabilize the body spin axis against mutation, dynamic imbalance and external torques.
摘要翻译：的方法和系统，用于稳定约在中间惯性轴线（Z）纺丝卫星是游离缺失盘。 A（22）组陀螺仪感测X分量和卫星体的角速度的Y分量。自由动量轮的单个度（26）具有与以存储动量相对于中间轴的固定横向取向。在一个中，实施例动量轮（26）被定向为平行动量存储于Y轴。转速计（30）感测的动量轮（26）的旋转速度。处理器（24）形成控制代表的控制转矩的一个信号将被施加到动量轮（26）。控制转矩基于X分量和所述卫星（20）的角速度的Y分量和动量轮（26）的角速度。这些方法和系统因此可以被用于反转纺丝卫星的自旋方向（20）确保翻滚恢复到优选的取向，和稳定身体自转轴针对突变，动态不平衡和外部扭矩。

42. 发明授权

EP0381574B1 Système de stabilisation mécanique à contre-rotation à rotors emboîtés 失效
标题翻译：反向旋转机械稳定系统插入转子。
公开(公告)号：EP0381574B1
公开(公告)日：1995-03-29
申请号：EP90400249.0
申请日：1990-01-30
申请人： SOCIETE EUROPEENNE DE PROPULSION
发明人： Atlas, Gérard
IPC分类号： G05D1/08
CPC分类号： G05D1/0883 , B64G1/283

43. 发明公开

EP0519038A1 PROCEDE DE CONTROLE D'ATTITUDE EN TANGAGE D'UN SATELLITE GRACE A LA PRESSION DE RADIATION SOLAIRE ET SATELLITE ADAPTE A SA MISE EN UVRE 失效转让
标题翻译：一种用于控制卫星被太阳风压，卫星NICK角度及其执行。
公开(公告)号：EP0519038A1
公开(公告)日：1992-12-23
申请号：EP92902322.0
申请日：1991-11-26
申请人： AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE
发明人： FLAMENT, Patrick , PERDU, Michel , PORTIER, Jean , BRUNET, Pierre
IPC分类号： B64G1 , F03H1
CPC分类号： B64G1/407 , B64G1/24 , B64G1/26 , B64G1/28 , B64G1/283 , B64G1/32 , B64G1/34 , B64G1/36 , B64G1/44 , B64G2001/245 , Y10S136/292
摘要： Un satellite comporte au moins une surface (4, 5) destinée principalement à être soumise au rayonnement solaire et s'étendant à partir du satellite selon une direction donnée (Y), un calculateur de bord (8) et, connectés à ce dernier, un système (7) de détection d'attitude, des moyens de contrôle d'orbite adaptés à appliquer au satellite des poussées selon des axes donnés et des moyens de contrôle d'attitude. Ce satellite comporte en outre des moyens (6') de commande en basculement de ladite surface parallèlement à une pluralité de plans contenant ladite direction donnée (donc notamment parallèlement au plan d'une aile de générateur solaire lorsque celle-ci constitue ladite surface). Ces moyens de commande en basculement étant commandés par ledit calculateur de bord. Ce basculement peut servir à générer un couple de tangage ou à amener le centre de gravité sur l'axe des moyens de contrôle d'orbite.

44. 发明授权

EP3931850B1 A SATELLITE SYSTEM 有权
公开(公告)号：EP3931850B1
公开(公告)日：2024-04-24
申请号：EP20763100.3
申请日：2020-02-25
IPC分类号： H01F6/04 , B64G1/00 , F25B9/14 , F25B9/00
CPC分类号： H01F6/04 , B64G1/283 , B33Y80/00 , B64G1/409 , B64G1/10 , B64G1/32 , H01F6/006 , H01F6/06

45. 发明公开

EP3346600A1 HIGH EFFICIENCY ACTUATOR FOR USE IN A MOMETUM CONTROL DEVICE 有权转让
公开(公告)号：EP3346600A1
公开(公告)日：2018-07-11
申请号：EP18150480.4
申请日：2018-01-05
申请人： Honeywell International Inc.
发明人： KRIEDER, Thom , GILREATH, John Douglas , STRONG, Ronald E. , VILLELA, Mark , HADDEN, Steven
IPC分类号： H02P6/08 , B64G1/28 , G05D1/08
CPC分类号： H02P6/17 , B64G1/283 , G05D1/0883 , H02P6/08 , H02P6/28
摘要： Methods and apparatus are provided for a controlled motor assembly for use in a reaction wheel assembly (RWA). The controlled motor assembly is optimized to work with an AC motor, and includes a filter configured to inhibit electrical and electromagnetic noise from being coupled between a spacecraft power bus and a power bus internal to the RWA, as well as an arrangement of power switch elements providing a path for motor phase currents associated with the AC motor. A digital control system is implemented to receive a command input, position sensor feedback and to retrieve parameters associated with the AC motor from a memory device. Based on the command input, the position sensor feedback and the parameters associated with the AC motor, the digital control system controls activation for the arrangement of power switch elements, and generates data output.

46. 发明公开

EP3259189A1 SATELLITE ARTIFICIEL 有权转让
公开(公告)号：EP3259189A1
公开(公告)日：2017-12-27
申请号：EP16733161.0
申请日：2016-06-01
申请人： Airbus Defence and Space SAS
发明人： WALKER, Andrew
IPC分类号： B64G1/22 , B64G1/50 , B64G1/10 , B64G1/42 , B64G1/58
CPC分类号： B64G1/503 , B64G1/10 , B64G1/226 , B64G1/283 , B64G1/402 , B64G1/425 , B64G1/58
摘要： The invention relates to an artificial satellite comprising an accumulator (62) apt to dissipate heat, at least one radiator (64) able to remove to space the heat dissipated by the accumulator (62), and a piece of equipment (52) that is said to be not very dissipative and that possesses an individual power density per unit area lower than 250 watts/m
2 , characterised in that it includes a thermally insulating cover (66) bounding, with said radiator (64), an isothermal interior zone (68) in which temperature is controlled by radiation, said accumulator (62) and said piece of not very dissipative equipment (52) being arranged under said thermally insulating cover (66), and in that said accumulator (62) has an operating range comprised between 0°C and 50°C and, preferably, between 10°C and 30°C.

47. 发明公开

EP2740668A3 Methods and apparatus for performing propulsion operations using electric propulsion systems 有权转让
标题翻译：使用电力推进系统执行推进操作的方法和设备
公开(公告)号：EP2740668A3
公开(公告)日：2017-12-27
申请号：EP13194767.3
申请日：2013-11-28
申请人： The Boeing Company
发明人： Peterka III, James J. , Caplin, Glenn N. , Aston, Richard W.
IPC分类号： B64G1/00 , B64G1/24 , B64G1/40 , B64G1/64 , B64G1/28 , B64G1/32 , B64G1/36 , B64G1/42 , B64G1/44 , B64G1/66
CPC分类号： B64G1/007 , B64G1/242 , B64G1/283 , B64G1/285 , B64G1/32 , B64G1/361 , B64G1/363 , B64G1/365 , B64G1/402 , B64G1/405 , B64G1/422 , B64G1/428 , B64G1/44 , B64G1/641 , B64G1/66
摘要： Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example apparatus includes a frame (207, 209), a power source (104) coupled to the frame and a payload (106)coupled to the frame, the payload to receive or transmit data. The apparatus also includes an electric propulsion system (108)coupled to the frame. The electric propulsion system is to enable attitude control, momentum control, and orbit control of the apparatus.
摘要翻译：公开了使用电力推进系统执行推进操作的方法和装置。示例装置包括帧（207,209），耦合到帧的电源（104）和耦合到帧的有效载荷（106），有效载荷用于接收或发送数据。该设备还包括耦合到框架的电力推进系统（108）。电力推进系统可以实现设备的姿态控制，动量控制和轨道控制。

48. 发明公开

EP3256381A1 SPACECRAFT ACTUATOR WHEEL WITH INTEGRATED BATTERY AND FUEL STORAGE 有权
标题翻译：具有集成电池和燃料储存的航天器执行器车轮
公开(公告)号：EP3256381A1
公开(公告)日：2017-12-20
申请号：EP16749796.5
申请日：2016-02-10
申请人： Novawurks, Inc.
发明人： JAEGER, Talbot
IPC分类号： B64G1/00 , B64G1/28 , B64G1/42 , G05D1/08
CPC分类号： B64G1/425 , B64G1/10 , B64G1/283 , B64G1/285 , B64G1/286 , B64G1/402 , B64G1/428 , B64G1/44 , B64G1/64 , B64G2001/1092
摘要： An improved spacecraft actuator wheel is provided which can be operated as a momentum wheel, a reaction wheel or a gimbal. The actuator wheel has a central cavity. One or more battery modules are located within the actuator wheel's central cavity. The battery modules supply power to one or more electronic components affixed to the actuator wheel or mounted on the spacecraft frame via an electrical harness. In addition, the actuator wheel's central cavity is pressurizeable for storing spacecraft propellant which can be controllably diverted to the spacecraft's thrusters through conduits and flow valves.

49. 发明公开

EP3254973A1 STACKABLE PANCAKE SATELLITE 有权
标题翻译：可堆叠的薄煎饼卫星
公开(公告)号：EP3254973A1
公开(公告)日：2017-12-13
申请号：EP17171562.6
申请日：2017-05-17
申请人： The Boeing Company
发明人： BUSCHE, Gregory Clayton
IPC分类号： B64G1/10 , B64G1/44 , B64G1/22
CPC分类号： B64G1/1085 , B64G1/10 , B64G1/22 , B64G1/283 , B64G1/40 , B64G1/44 , B64G2700/66
摘要： A stackable pancake satellite that is configured so that a plurality of the satellites can be stacked within a payload fairing of a launch vehicle. Each satellite includes sections that are folded or rotated together prior to launch, and unfolded or rotated away from each other when deployed. A first section is a satellite body having a first side that acts as a thermal radiator and a second side opposite the first side that includes an antenna. A second section includes one or more solar panels attached adjacent to the first side of the satellite body. A third section includes a splash plate reflector attached adjacent to the second side of the satellite body that reflects signals between Earth and the antenna. When deployed, the solar panels are pointed towards the Sun and the splash plate reflector directs the signals between the Earth and the antenna.
摘要翻译：一种可堆叠的煎饼卫星，其构造成使得多个卫星可堆叠在运载火箭的有效载荷整流罩内。每个卫星包括在发射前一起折叠或旋转的部分，并且在展开时展开或旋转离开彼此。第一部分是卫星主体，其具有用作散热器的第一侧和与包括天线的第一侧相对的第二侧。第二部分包括邻近卫星主体的第一侧附接的一个或多个太阳能电池板。第三部分包括邻近卫星主体的第二侧附着的反射板反射器，反射地球和天线之间的信号。部署时，太阳能电池板指向太阳，防溅板反射器指示地球和天线之间的信号。

50. 发明授权

EP2224307B1 Spacecraft Acquisiton Maneuvers Using Position-Based Gyroless Control 有权
标题翻译：航天器采集机动使用基于位置的无陀螺仪控制
公开(公告)号：EP2224307B1
公开(公告)日：2017-10-04
申请号：EP10250166.5
申请日：2010-02-01
申请人： The Boeing Company
发明人： Liu, Dan Y. , Chiang, Richard Y.
IPC分类号： B64G1/26 , B64G1/36 , G05D1/08 , B64G1/24 , B64G1/28
CPC分类号： B64G1/26 , B64G1/283 , B64G1/36 , B64G1/361 , B64G2001/245 , G05D1/0883

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