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81. 发明申请

US20100314499A1 ACTUATOR WITH TRANSFER OF ANGULAR MOMENTUM FOR THE ATTITUDE CONTROL OF A SPACECRAFT 有权
标题翻译：具有转移角度的运动员用于空间的姿态控制
公开(公告)号：US20100314499A1
公开(公告)日：2010-12-16
申请号：US12744174
申请日：2008-11-18
申请人： Jean Sperandei
发明人： Jean Sperandei
IPC分类号： B64G1/28
CPC分类号： B64G1/283 , B64G1/28 , B64G1/285 , B64G1/286
摘要： An attitude control actuator of a spacecraft includes a first momentum wheel driven in rotation by a motor and a second momentum wheel. Both momentum wheels are movable in rotation about an axis and are mechanically coupled by coupling means imposing between a rotation speed ω1 of the first momentum wheel and a rotation speed ω2 of the second momentum wheel a ratio R=ω2/ω1, negative on the one hand and continuously modifiable by the coupling means in response to a command on the other hand so as to modify the total angular momentum of the actuator while the total kinetic energy of the wheels are kept constant. In one embodiment, both momentum wheels have the same inertia and are coupled through a toroidal variator, where ratio R varies between −3 and −1/3. The motor drives the momentum wheels and operates as a generator for braking the momentum wheels.
摘要翻译：航天器的姿态控制致动器包括由马达和第二动量轮旋转驱动的第一动量轮。两个动量轮可以围绕轴线旋转运动，并且通过在第一动量轮的旋转速度ω1和第二动量轮的转速ω2之间的耦合装置机械耦合，比率R =ω2/ω1为负的响应于另一方面的命令，通过联接装置可连续地修改，以便在轮的总动能保持恒定的同时修改致动器的总角动量。在一个实施例中，两个动量轮具有相同的惯性，并且通过环形变换器耦合，其中比率R在-3和-1/3之间变化。电动机驱动动量轮并作为用于制动动量轮的发电机运行。

82. 发明授权

US07665695B2 Unified attitude control for spacecraft transfer orbit operations 有权
标题翻译：航天器转移轨道作战统一态度控制
公开(公告)号：US07665695B2
公开(公告)日：2010-02-23
申请号：US11199932
申请日：2005-08-09
申请人： H. Grant Wang , Rongsheng Li
发明人： H. Grant Wang , Rongsheng Li
IPC分类号： B64G1/24
CPC分类号： B64G1/281 , B64G1/00 , B64G1/007 , B64G1/10 , B64G1/24 , B64G1/242 , B64G1/26 , B64G1/28 , B64G1/283 , B64G1/285 , B64G1/288 , B64G1/36 , B64G1/361 , B64G1/363 , B64G1/40 , B64G1/401 , B64G1/405 , B64G1/44 , B64G1/443 , G01C21/02 , G01C21/025 , G05D1/08 , G05D1/0883
摘要： A method of controlling attitude of a spacecraft during a transfer orbit operation is provided. The method includes providing a slow spin rate, determining the attitude of the spacecraft using a unified sensor set, and controlling the attitude of the spacecraft using a unified control law. The use of a unified set of sensors and a unified control law reduces spacecraft complexity, cost, and weight.
摘要翻译：提供了一种在转移轨道操作期间控制航天器姿态的方法。该方法包括提供缓慢的旋转速率，使用统一的传感器组来确定航天器的姿态，并使用统一的控制律来控制航天器的姿态。使用统一的传感器和统一的控制规则可以降低航天器的复杂性，成本和重量。

83. 发明申请

US20100007303A1 Torquer Apparatus 有权
标题翻译：手套装置
公开(公告)号：US20100007303A1
公开(公告)日：2010-01-14
申请号：US12296096
申请日：2007-03-28
申请人： Olivier Chételat
发明人： Olivier Chételat
IPC分类号： H02K1/27 , H02K1/12 , H02P6/18 , H02K29/10 , H02P6/08
CPC分类号： G01C19/30 , B64G1/28 , H02K16/00 , H02K21/12 , H02K41/031 , H02K2201/03 , H02K2201/18 , Y10T74/1254
摘要： A torquer apparatus generally comprises a reaction-gyro sphere consisting of a concentric assembly of a substantially spherical rotor and a substantially spherical stator. This is implemented in the present invention as a rotor with magnetic poles such that, when radially projected on a concentric octahedron, the same symmetrical pattern is obtained on all faces of said octahedron, the polarity of the poles projected on two adjacent faces of said octahedron being opposite and a stator with at least twenty poles magnetized with coils and such that, when radially projected on a concentric icosahedron, the same symmetrical pattern is obtained on all faces of said icosahedron, said stator being-in nominal position-concentric with said rotor. Real-time measurements, or equivalent information, of the position of the rotor with respect to the stator are obtained together with exported torque from the stator, or the orientation of the rotor with respect to the stator. A controller controls the current in the coils of the stator poles based on said measurements, or said equivalent information, such that the rotor is magnetically held in said nominal position, and that the desired torque is exported.
摘要翻译：矫正装置通常包括由基本上球形的转子和基本上球形的定子的同心组件组成的反作用陀螺仪球体。这在本发明中被实现为具有磁极的转子，使得当径向地突出在同心八面体上时，在所述八面体的所有面上获得相同的对称图案，所述八极八面体的两个相邻面上的极性极性相对的定子和具有线圈磁化的至少二十个极的定子，并且当径向地突出在同心二十面体上时，在所述二十面体的所有面上都获得相同的对称图案，所述定子位于与所述转子同心的标称位置。获得转子相对于定子的位置的实时测量或等效信息，以及来自定子的输出扭矩或转子相对于定子的取向。控制器基于所述测量或所述等效信息来控制定子极线圈中的电流，使得转子被磁力地保持在所述标称位置，并且输出期望的扭矩。

84. 发明授权

US07464902B2 Satellite with electromagnetic control of objects 有权
标题翻译：卫星与物体的电磁控制
公开(公告)号：US07464902B2
公开(公告)日：2008-12-16
申请号：US11095504
申请日：2005-04-01
申请人： Xavier Leyre , Hervé Sainct
发明人： Xavier Leyre , Hervé Sainct
IPC分类号： B64G1/66
CPC分类号： B64G1/24 , B64G1/26 , B64G1/28 , B64G1/288 , B64G1/32 , B64G1/36 , B64G1/366 , B64G1/66
摘要： A satellite comprises a main body and, in orbit, at least one free object floating in space including a portion of the payload transferred from the main body. The free object is restricted to a precise position and attitude relative to the main body. An electromagnetic force and an electromagnetic torque are produced for controlling the position and the attitude of the free object in accordance with a master-slave relationship.
摘要翻译：卫星包括主体，并且在轨道上，浮动在空间中的至少一个自由物体，包括从主体传送的有效载荷的一部分。自由物体被限制在相对于主体的精确位置和姿态。产生电磁力和电磁转矩，用于根据主从关系来控制自由物体的位置和姿态。

85. 发明申请

US20080228332A1 ACTIVE CONTROL OF SOFT HYBRID ISOLATION SYSTEMS 有权
标题翻译：软混合隔离系统的主动控制
公开(公告)号：US20080228332A1
公开(公告)日：2008-09-18
申请号：US11687551
申请日：2007-03-16
申请人： Timothy A. Hindle , Brian J. Hamilton , Louis R. Jackson
发明人： Timothy A. Hindle , Brian J. Hamilton , Louis R. Jackson
IPC分类号： B64G1/24 , G05B13/02
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. One apparatus includes a non-contacting actuator and a passive mechanical system coupled in parallel with one another. A system includes a payload, a bus, and a hybrid actuator 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 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 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 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的运动。一种装置包括彼此并联连接的非接触致动器和被动机械系统。一种系统包括有效载荷，总线和包括非接触致动器和并联耦合的无源机械系统并且耦合在总线和有效载荷之间的混合致动器。该系统还包括惯性致动器，其构造成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。

86. 发明授权

US07410130B2 Star-tracker-based attitude determination for spinning spacecraft 有权
标题翻译：用于旋转航天器的基于星际追踪器的姿态测定
公开(公告)号：US07410130B2
公开(公告)日：2008-08-12
申请号：US10910430
申请日：2004-08-03
申请人： H. Grant Wang , David D. Needelman , Arun Prakash
发明人： H. Grant Wang , David D. Needelman , Arun Prakash
IPC分类号： B64G1/24
CPC分类号： B64G1/281 , B64G1/007 , B64G1/242 , B64G1/26 , B64G1/28 , B64G1/283 , B64G1/285 , B64G1/288 , B64G1/36 , B64G1/361 , B64G1/363 , B64G1/401 , B64G1/405 , B64G1/44 , B64G1/443 , G01C21/025 , G05D1/0883
摘要： A method of determining the attitude of a spinning spacecraft is provided. The method includes stabilizing the spacecraft, initializing the attitude of the spacecraft using star tracker data, and estimating the attitude of the spacecraft.
摘要翻译：提供了一种确定旋转航天器姿态的方法。该方法包括稳定航天器，使用星形跟踪器数据初始化航天器的姿态，并估计航天器的姿态。

87. 发明授权

US07343829B1 Shaftless gyrostabilizer for aerial platforms 失效
标题翻译：用于高空作业车的无轴陀螺稳定器
公开(公告)号：US07343829B1
公开(公告)日：2008-03-18
申请号：US11036492
申请日：2005-01-14
申请人： William E. Inman
发明人： William E. Inman
IPC分类号： G01C19/30 , G01C19/46 , G01C19/34
CPC分类号： G01C21/18 , B64G1/28 , Y10T74/1243 , Y10T74/1289
摘要： Gyrostabilizer methods and apparatus having simultaneously counter-revolving masses that do not require physical shafts or axles. The stabilizer can have dual counter-revolving concentric rings, or tracks filled with weights such as spherical balls, that are propelled in orbital fashion by fluid pressure or electromagnet propulsion. The rings can include rigid contiguous rings, such as metal, plastic, composites, and the like. Additionally, the rings can include liquids and/or gasses. Still furthermore, the rings can include flexible, bendable contiguous materials, such as chains and ropes. The concentric ring diameters can be a few inches to more than ten (10) feet. Without an axle or shaft the weight of the gyrostabilizer is shifted to the perimeter where most of the momentum is generated at a fraction of the weight of gyrostabilizers that spin on an axle. The gyrostabilizer can dampen unsteadiness such as tremors, vibrations, sway, pitch, roll, and yaw.
摘要翻译：具有同时具有不需要物理轴或轴的反向旋转质量的Gyrostabilizer方法和装置。稳定器可以具有双重反向旋转的同心环或充满重量（例如球形球）的轨道，其通过流体压力或电磁推进以轨道方式推进。环可以包括刚性连续的环，例如金属，塑料，复合材料等。另外，环可以包括液体和/或气体。此外，环可以包括柔性的，可弯曲的连续材料，例如链条和绳索。同心环直径可以是几英寸到十（10）英尺。在没有轴或轴的情况下，陀螺稳定器的重量被转移到周边，其中大部分动量是在旋转轴上的陀螺仪的重量的一部分产生的。陀螺稳定器可以抑制震动，振动，摇摆，俯仰，滚动和偏航等不稳定性。

88. 发明申请

US20060186274A1 Spacecraft power acquisition method for wing-stowed configuration 有权
公开(公告)号：US20060186274A1
公开(公告)日：2006-08-24
申请号：US11200215
申请日：2005-08-09
申请人： H. Wang , Rongsheng Li
发明人： H. Wang , Rongsheng Li
IPC分类号： B64G1/10
CPC分类号： B64G1/281 , B64G1/007 , B64G1/242 , B64G1/26 , B64G1/28 , B64G1/283 , B64G1/285 , B64G1/288 , B64G1/36 , B64G1/361 , B64G1/363 , B64G1/401 , B64G1/405 , B64G1/44 , B64G1/443 , G01C21/025 , G05D1/0883
摘要： A system for, and method of recovering a solar-powered spacecraft from an anomaly that renders the attitude of the spacecraft unknown includes maintaining a power-safe attitude by switching between two orthogonal axes using solar panel current sensors. The system and method may also include simultaneously determining spacecraft attitude using a star sensor. The system is applicable to spacecraft operating in a solar wing-stowed configuration.

89. 发明申请

US20030171855A1 SPACECRAFT METHODS AND STRUCTURES WITH ENHANCED ATTITUDE CONTROL THAT FACILITATES GYROSCOPE SUBSTITUTIONS 有权
标题翻译：具有增强姿态控制的补充方法和结构，有助于取代GYROSCOPE
公开(公告)号：US20030171855A1
公开(公告)日：2003-09-11
申请号：US10039488
申请日：2001-10-28
申请人： BOEING COMPANY
发明人： Rongsheng Li , Jeffrey A. Kurland , Alec M. Dawson , Yeong-Wei A. Wu , David S. Uetrecht
IPC分类号： G05D001/00 , G06F007/00
CPC分类号： G05D1/0883 , B64G1/26 , B64G1/28 , B64G1/285 , B64G1/288 , B64G1/32 , B64G1/36 , G05B13/024
摘要： Methods and structures are provided that enhance attitude control during gyroscope substitutions by insuring that a spacecraft's attitude control system does not drive its absolute-attitude sensors out of their capture ranges. In a method embodiment, an operational process-noise covariance Q of a Kalman filter is temporarily replaced with a substantially greater interim process-noise covariance Q. This replacement increases the weight given to the most recent attitude measurements and hastens the reduction of attitude errors and gyroscope bias errors. The error effect of the substituted gyroscopes is reduced and the absolute-attitude sensors are not driven out of their capture range. In another method embodiment, this replacement is preceded by the temporary replacement of an operational measurement-noise variance R with a substantially larger interim measurement-noise variance R to reduce transients during the gyroscope substitutions.
摘要翻译：提供了通过确保航天器的姿态控制系统不将其绝对姿态传感器驱动到其捕获范围之外来增强陀螺仪替换期间的姿态控制的方法和结构。在方法实施例中，卡尔曼滤波器的操作过程 - 噪声协方差Q被临时过程噪声协方差Q临时替换。该替换增加了给予最近姿态测量的重量并加速了姿态误差的降低，并且陀螺偏置误差。取代陀螺仪的误差效应降低，绝对姿态传感器不会被驱赶出其捕获范围。在另一方法实施例中，该替换之前是临时替换具有相当大的临时测量噪声方差R的操作测量噪声方差R，以减少在陀螺仪替换期间的瞬变。

90. 发明授权

US06568291B1 Shaftless gyrostabilizer 失效
标题翻译：无轴陀螺稳定器
公开(公告)号：US06568291B1
公开(公告)日：2003-05-27
申请号：US09680495
申请日：2000-10-05
申请人： William E. Inman
发明人： William E. Inman
IPC分类号： G01C1902
CPC分类号： B64G1/285 , B64G1/28 , B64G1/286 , Y10T74/1221 , Y10T74/1229 , Y10T74/125 , Y10T74/1296
摘要： A gyrostabilizer without a physical shaft or axle is constructed. The stabilizer has dual counter-revolving concentric rings filled with weights such as spherical balls that are propelled in orbital fashion by fluid pressure or electromagnet propulsion. The diameter of the concentric ring can vary from a few inches to more than ten (10) feet. Without an axle or shaft the weight of the gyrostabilizer is shifted to the perimeter where most of the momentum is generated at a fraction of the weight of gyrostabilizers that spin on an axle. Also without an axle or shaft the space between the center of revolution and the revolving balls is usable or void. When properly mounted in a vehicle or structure unsteadiness such as tremors, vibrations, sway, pitch, roll, yaw can be dampened.
摘要翻译：没有物理轴或轴的陀螺稳定器被构造。稳定器具有双重反向旋转的同心环，其中装有诸如通过流体压力或电磁推进以轨道方式推进的球形球的重量。同心环的直径可以从几英寸到十（10）英尺不等。在没有轴或轴的情况下，陀螺稳定器的重量被转移到周边，其中大部分动量是在旋转轴上的陀螺仪的重量的一部分产生的。也没有轴或轴，旋转中心和旋转球之间的空间可用或无效。当正确地安装在车辆或结构中时，诸如震颤，振动，摇摆，俯仰，滚动，偏航的不稳定性可以被抑制。

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