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    CubeSat System, Method and Apparatus
    3.
    发明申请
    CubeSat System, Method and Apparatus 有权
    CubeSat系统，方法和装置

    公开(公告)号：US20150039879A1

    公开(公告)日：2015-02-05

    申请号：US14517592

    申请日：2014-10-17

    申请人： Cal Poly Corporation

    发明人： Jordi Puig-Suari ,  Austin Williams

    IPC分类号： B64G1/66 ,  G06F9/44

    CPC分类号： B64G1/66 ,  B64G1/10 ,  B64G1/288 ,  B64G1/32 ,  B64G1/363 ,  B64G1/366 ,  B64G1/428 ,  B64G1/546 ,  B64G2001/1092 ,  G06F9/4406

    摘要： A satellite system includes a chassis, an avionics package included within an upper portion of the chassis. The avionics package includes a main system board, a payload interface board, at least one daughter board and a battery board. The main system board, the payload interface board, the at least one daughter board, and the battery board reside in substantially parallel planes. The payload interface board, the at least one daughter board, and the battery board are coupled to the main system board through one or more stackable connectors. A method of operating a satellite is also described.

    摘要翻译： 卫星系统包括机箱，包括在机箱的上部内的航空电子设备组件。 航空电子组件包括主系统板，有效载荷接口板，至少一个子板和电池板。 主系统板，有效载荷接口板，至少一个子板和电池板位于基本平行的平面中。 有效负载接口板，至少一个子板和电池板通过一个或多个可堆叠连接器耦合到主系统板。 还描述了操作卫星的方法。

    Method and computer program product for controlling inertial attitude of an artificial satellite by applying gyroscopic precession to maintain the spin axis perpendicular to sun lines
    4.
    发明授权
    Method and computer program product for controlling inertial attitude of an artificial satellite by applying gyroscopic precession to maintain the spin axis perpendicular to sun lines 失效
    方法和计算机程序产品，用于通过应用陀螺进动来控制人造卫星的惯性姿态，以保持旋转轴垂直于太阳线

    公开(公告)号：US08706322B2

    公开(公告)日：2014-04-22

    申请号：US13212433

    申请日：2011-08-18

    申请人： William M. Johnson

    发明人： William M. Johnson

    IPC分类号： B64G1/32 ,  B64G1/36 ,  G05D1/08

    CPC分类号： B64G1/281 ,  B64G1/1007 ,  B64G1/1085 ,  B64G1/242 ,  B64G1/32 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365 ,  B64G1/44 ,  G01S3/7862 ,  G01S3/7867 ,  G05D1/0883

    摘要： A method of controlling inertial attitude of an artificial satellite in order to perform a navigation function and to maximize terrestrial coverage of the Earth by the satellite. The method includes deploying the artificial satellite in an orbit about the poles of the Earth; applying gyroscopic precession to the artificial satellite spin axis to precess and maintain the satellite near the ecliptic pole; deploying the artificial satellite so that the spin axis is initially perpendicular to or substantially perpendicular to sun lines; and applying gyroscopic precession to the artificial satellite spin axis to precess the spin axis away from an initial deployed attitude at a selectively-variable precession rate and to maintain the spin axis perpendicular to or substantially perpendicular to the sun lines.

    摘要翻译： 控制人造卫星的惯性姿态以便执行导航功能并使卫星的地球覆盖范围最大化的方法。 该方法包括将人造卫星部署在围绕地球两极的轨道上; 对人造卫星旋转轴进行陀螺进动，以使卫星靠近黄道; 部署人造卫星使得旋转轴线最初垂直于或基本垂直于太阳线; 以及将陀螺进动应用于人造卫星旋转轴线，以使旋转轴线以选择性可变的进动速率远离初始展开姿态，并保持旋转轴垂直于或基本垂直于太阳线。

    Method For Reducing the Angular Momentum and Controlling the Attitude of a Spacecraft
    6.
    发明申请
    Method For Reducing the Angular Momentum and Controlling the Attitude of a Spacecraft 有权
    降低角动量和控制航天器姿态的方法

    公开(公告)号：US20140032022A1

    公开(公告)日：2014-01-30

    申请号：US13945821

    申请日：2013-07-18

    申请人： Thales

    发明人： François CAULLIER ,  Faustine DELHAY ,  Jean-Marc LACAMBRE ,  Etienne BROUILLARD

    IPC分类号： B64G1/28

    CPC分类号： B64G1/288 ,  B64G1/007 ,  B64G1/24 ,  B64G1/26 ,  B64G1/283 ,  B64G1/285 ,  B64G1/286 ,  B64G1/36 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365 ,  B64G1/405 ,  B64G2001/245 ,  G05D1/0883

    摘要： A method for reducing the angular momentum of a spacecraft comprises a propulsion device able to generate a torque along a Z axis corresponding to an axis of maximum inertia or minimum inertia of the spacecraft, an X axis and a Y axis forming with Z an orthogonal frame; an angular momentum accumulating device, able to generate an angular momentum and a torque along the three axes; and a set of sensors able to measure the angular velocities and estimate the angular momentum of the spacecraft. The method comprises a first step of aligning the angular momentum of the spacecraft along the Z axis, consisting in slaving the angular momentum of the angular momentum accumulating device to the angular velocity of the spacecraft, and a second step of reducing the angular momentum of the spacecraft using a torque generated by the propulsion device.

    摘要翻译： 用于减小航天器的角动量的方法包括能够产生沿着Z轴对应于航天器的最大惯量或最小惯性的轴的扭矩的推进装置，X轴和Y轴形成正交框架 ; 角动量积存装置，能够沿着三个轴产生角动量和扭矩; 以及能够测量角速度并估计航天器的角动量的一组传感器。 该方法包括使沿着Z轴的航天器的角动量对准的第一步骤，其包括将角动量积存装置的角动量沿着航空器的角速度降低，以及第二步骤， 航天器使用由推进装置产生的扭矩。

    Systems and Methods for a Self-Deploying Vehicle Drag Device
    7.
    发明申请
    Systems and Methods for a Self-Deploying Vehicle Drag Device 有权
    自动部署车辆拖动装置的系统和方法

    公开(公告)号：US20130032667A1

    公开(公告)日：2013-02-07

    申请号：US13197333

    申请日：2011-08-03

    申请人： Brian S. Hardy ,  Jerome K. Fuller

    发明人： Brian S. Hardy ,  Jerome K. Fuller

    IPC分类号： B64D17/80 ,  B60T1/16

    CPC分类号： B60T1/16 ,  B64G1/363 ,  B64G1/365 ,  B64G1/44 ,  B64G1/62 ,  B64G1/648 ,  F16D63/00

    摘要： Embodiments of the invention relate to systems and methods for a self-deploying vehicle drag device. In one embodiment, a drag device for a vehicle can be provided. The drag device can include a chute body, wherein the chute body is connected to the vehicle. The drag device can also include at least one collapsible member mounted to the chute body, wherein the at least one collapsible member and chute body are maintained in respective compressed configurations until deployed. Furthermore, the drag device can include at least one device adapted to release the chute body from the vehicle, wherein the chute body and the at least one collapsible member are deployed in expanded configurations with respect to the vehicle.

    摘要翻译： 本发明的实施例涉及一种用于自身部署车辆拖拉装置的系统和方法。 在一个实施例中，可以提供用于车辆的牵引装置。 牵引装置可以包括滑槽体，其中滑槽主体连接到车辆。 牵引装置还可以包括安装到滑槽主体的至少一个可折叠构件，其中至少一个可折叠构件和滑槽本体保持在相应的压缩构型中直到展开。 此外，牵引装置可以包括适于将滑槽主体从车辆释放的至少一个装置，其中滑槽主体和至少一个可折叠构件以相对于车辆的扩展构型展开。

    METHODS AND SYSTEMS FOR ADJUSTING ATTITUDE USING REACTION WHEELS
    8.
    发明申请
    METHODS AND SYSTEMS FOR ADJUSTING ATTITUDE USING REACTION WHEELS 有权
    使用反应轮调整姿态的方法和系统

    公开(公告)号：US20120325970A1

    公开(公告)日：2012-12-27

    申请号：US13168700

    申请日：2011-06-24

    申请人： Brian Hamilton

    发明人： Brian Hamilton

    IPC分类号： B64G1/28 ,  G05D1/00

    CPC分类号： B64G1/283 ,  B64G1/288 ,  B64G1/361 ,  B64G1/363 ,  G05D1/0883 ,  H02P6/06

    摘要： Methods and systems are provided for controlling attitude of a vehicle using a reaction wheel onboard the vehicle. One exemplary method involves receiving a torque command for adjusting the attitude of the vehicle using the reaction wheel, determining a phase error of the reaction wheel based at least in part on the torque command, and determining a motor torque command for the reaction wheel based on the phase error. The motor torque command is provided to an electric motor of the reaction wheel to apply a corresponding torque to the rotor of the reaction wheel. The relationship between the magnitude of the motor torque command and the magnitude of the phase error is nonlinear. In exemplary embodiments, the magnitude of the motor torque command exceeds the stiction torque, at least instantaneously, when the reaction wheel has fallen behind an expected position by more than a threshold amount.

    摘要翻译： 提供了用于控制使用车辆上的反作用轮的车辆姿态的方法和系统。 一种示例性方法包括接收用于使用反作用轮调节车辆姿态的扭矩指令，至少部分地基于转矩指令确定反作用轮的相位误差，并且基于 相位误差。 电动机转矩指令被提供给反作用轮的电动机，以将相应的扭矩施加到反作用轮的转子。 电动机转矩指令的大小与相位误差的大小之间的关系是非线性的。 在示例性实施例中，当反作用轮已经落下预期位置超过阈值量时，马达转矩指令的幅度至少瞬时地超过静摩擦转矩。

    Method and device for calibration of digital celestial sensor
    10.
    发明授权
    Method and device for calibration of digital celestial sensor 有权
    数字天体传感器校准方法和装置

    公开(公告)号：US07822572B2

    公开(公告)日：2010-10-26

    申请号：US12036888

    申请日：2008-02-25

    申请人： Guangjun Zhang ,  Xinguo Wei ,  Qiaoyun Fan ,  Jie Jiang

    发明人： Guangjun Zhang ,  Xinguo Wei ,  Qiaoyun Fan ,  Jie Jiang

    IPC分类号： G01C25/00

    CPC分类号： G01S3/7867 ,  B64G1/361 ,  B64G1/363

    摘要： A method for calibration of a digital celestial sensor is disclosed. First, an integrated mathematic model for imaging of a celestial sensor is established according to external and internal parameters of the calibration system of the celestial sensor. Second, by rotating two axes of a rotator by different angles, calibration points data are acquired and sent to a processing computer through an interface circuit. Finally, a two-step calibration program is implemented to calculate the calibration parameters by substituting calibration points' data to the integrated mathematic model. An application device of the calibration method is also provided. The device may include a celestial simulator to provide simulated sunlight or starlight, a two-axis rotator to acquire different calibration points' data, and a processing computer to record the calibration points' data and calculate the calibration parameters.

    摘要翻译： 公开了一种用于校准数字天体传感器的方法。 首先，根据天体传感器校准系统的外部参数和内部参数建立了天体传感器成像的综合数学模型。 第二，通过旋转不同角度旋转两个轴，获取校准点数据，并通过接口电路发送到处理计算机。 最后，通过将校准点的数据代入综合数学模型，实施了两步校准程序来计算校准参数。 还提供了校准方法的应用装置。 该装置可以包括用于提供模拟太阳光或星光的天体模拟器，用于获取不同校准点数据的双轴旋转器，以及记录校准点数据并计算校准参数的处理计算机。