公开(公告)号：US20100059631A1

公开(公告)日：2010-03-11

申请号：US12611658

申请日：2009-11-03

申请人： H. Grant Wang ,  Rongsheng Li

发明人： H. Grant Wang ,  Rongsheng Li

IPC分类号： B64G1/26 ,  B64G1/36 ,  B64G1/28 ,  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。

公开(公告)号：US20100019092A1

公开(公告)日：2010-01-28

申请号：US12178440

申请日：2008-07-23

申请人： Dan Y. Liu ,  Qinghong W. Wang ,  Richard Y. Chiang

发明人： Dan Y. Liu ,  Qinghong W. Wang ,  Richard Y. Chiang

IPC分类号： B64G1/38

CPC分类号： B64G1/281 ,  B64G1/283 ,  B64G1/285 ,  B64G1/286 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365 ,  B64G1/366 ,  B64G1/38 ,  G05D1/0883

摘要： A system for damping nutation and removing wobble of a spacecraft spinning about a given axis is provided. She system includes a sensor configured to determine three dimensional attitude measurements of the spacecraft, a processor operatively coupled to the sensor and configured to execute a process that facilitates aligning the spin axis with a spacecraft momentum vector. The processor, when executing the process, is programmed to receive spacecraft attitude data from the sensor, determine a torque command using the received attitude data, and control a momentum storage actuator on the spacecraft using the determined torque command such that an angular deviation about the given axis is reduced.

摘要翻译： 提供了一种用于阻尼章动和消除围绕给定轴线旋转的航天器摆动的系统。 她的系统包括被配置为确定航天器的三维姿态测量的传感器，可操作地耦合到传感器并被配置为执行便于将旋转轴与航天器动量向量对准的过程的处理器。 处理器在执行该过程时被编程为从传感器接收航天器姿态数据，使用接收的姿态数据确定扭矩指令，并且使用所确定的扭矩命令来控制航天器上的动量存储致动器，使得围绕 给定轴减少。

公开(公告)号：US07588213B2

公开(公告)日：2009-09-15

申请号：US11703287

申请日：2007-02-07

申请人： Robert F. D'Ausilio ,  James R. Stuart ,  Bari M. Southard ,  Franklin H. Williams, Jr.

发明人： Robert F. D'Ausilio ,  James R. Stuart ,  Bari M. Southard ,  Franklin H. Williams, Jr.

IPC分类号： B64G1/40 ,  B64G1/42

CPC分类号： B64G1/1078 ,  B64G1/007 ,  B64G1/222 ,  B64G1/242 ,  B64G1/283 ,  B64G1/288 ,  B64G1/363 ,  B64G1/405 ,  B64G1/406 ,  B64G1/408 ,  B64G1/422 ,  B64G1/44 ,  B64G1/503 ,  B64G1/646 ,  B64G1/66

摘要： A preferred In Orbit Transportation & Recovery System (IOSTAR™) (10) includes a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

公开(公告)号：US07216036B2

公开(公告)日：2007-05-08

申请号：US10621097

申请日：2003-07-16

申请人： Tye M. Brady ,  Anthony S. Kourepenis ,  William F. Wyman, Jr.

发明人： Tye M. Brady ,  Anthony S. Kourepenis ,  William F. Wyman, Jr.

IPC分类号： G01C21/00

CPC分类号： G01C21/165 ,  B64G1/288 ,  B64G1/361 ,  B64G1/363 ,  G01C21/025

摘要： An integrated inertial stellar attitude sensor for an aerospace vehicle includes a star camera system, a gyroscope system, a controller system for synchronously integrating an output of said star camera system and an output of said gyroscope system into a stream of data, and a flight computer responsive to said stream of data for determining from the star camera system output and the gyroscope system output the attitude of the aerospace vehicle.

摘要翻译： 用于航空航天车辆的集成的惯性恒星姿态传感器包括星形摄像机系统，陀螺仪系统，用于将所述星形摄像机系统的输出和所述陀螺仪系统的输出同步地集成为数据流的控制器系统，以及飞行计算机 响应于所述数据流，用于从星形摄像机系统输出确定并且陀螺仪系统输出航空航天车辆的姿态。

公开(公告)号：US20040113020A1

公开(公告)日：2004-06-17

申请号：US10318715

申请日：2002-12-13

申请人： THE BOEING COMPANY

发明人： Hanching Grant Wang ,  Richard A. Fowell ,  Che-Hang C. Ih

IPC分类号： B64G001/28

CPC分类号： B64G1/407 ,  B64G1/222 ,  B64G1/242 ,  B64G1/26 ,  B64G1/283 ,  B64G1/285 ,  B64G1/32 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365 ,  B64G1/443 ,  B64G1/66

摘要： A method and an apparatus for controlling the attitude and momentum of a spacecraft while deploying an appendage from the spacecraft. The method uses solar tacking and similar techniques to produce differential solar torques that are used to control the momentum and attitude of the spacecraft during the appendage deployment.

摘要翻译： 一种用于在从航天器部署附件的同时控制航天器的姿态和动量的方法和装置。 该方法使用太阳能固定和类似技术来产生差分太阳能转矩，用于控制附件部署期间航天器的动量和姿态。

公开(公告)号：US06616104B1

公开(公告)日：2003-09-09

申请号：US10177110

申请日：2002-06-24

申请人： Gen-Sen James Cheng ,  Neil Evan Goodzeit

发明人： Gen-Sen James Cheng ,  Neil Evan Goodzeit

IPC分类号： B64G100

CPC分类号： B64G1/1007 ,  B64G1/24 ,  B64G1/242 ,  B64G1/363 ,  B64G1/365 ,  B64G1/44 ,  B64G1/503

摘要： A method for controlling a geosynchronous spacecraft. A yaw axis and a roll axis of the spacecraft are oriented parallel to the earth equatorial plane. A coordinate frame of a payload is rotated about a minus roll axis of the spacecraft at an angle equivalent to an orbit inclination of the spacecraft, thereby maintaining elements of a payload pointing toward a desired region on the earth. A spacecraft attitude is corrected to maintain the payload elements pointing at the desired region on the earth.

摘要翻译： 一种控制地球同步航天器的方法。 飞行器的偏转轴和滚动轴线平行于赤道平面定向。 有效载荷的坐标系以与航天器的轨道倾斜度相等的角度围绕航天器的负滚轴轴线旋转，从而将有效载荷的元件指向地球上所需的区域。 校正航天器的姿态，以保持有效载荷元件指向地球上所需的区域。

公开(公告)号：US06561462B1

公开(公告)日：2003-05-13

申请号：US10081468

申请日：2002-02-21

申请人： Hanching G. Wang ,  Umesh Ketkar ,  Albert A. Munoz ,  Sadek Mansour

发明人： Hanching G. Wang ,  Umesh Ketkar ,  Albert A. Munoz ,  Sadek Mansour

IPC分类号： B64G136

CPC分类号： B64G1/363 ,  B64G2001/245

摘要： A spacecraft power/sun acquisition method includes a pitch search phase in which the spacecraft is rotated about a pitch axis, stopped, quaternions reset to remember position, and yaw search phase is entered when a first TOA occurs from a first slit sun sensor, and a keyhole slew is performed when the first TOA does not occur. The method also includes yaw search phase in which a keyhole slew is performed by rotating the spacecraft about a yaw axis, stopping the spacecraft, and entering pitch search phase when the first TOA does not occur, and in which the spacecraft is rotated about a yaw axis, stopped, quaternions reset, and sun hold phase is entered when a second TOA occurs from a second slit sun sensor. Lastly, the method includes a sun hold phase in which the spacecraft is oriented to the sun and placed in spin at power safe attitude.

摘要翻译： 航天器功率/太阳采集方法包括：俯仰搜索阶段，其中航天器围绕俯仰轴线旋转，停止，四元数复位为记忆位置，并且当第一狭缝太阳传感器发生第一TOA时进入偏航搜索阶段，以及 当不发生第一个TOA时执行锁孔旋转。 该方法还包括偏航搜索阶段，其中通过围绕偏转轴旋转航天器，停止航天器并且当第一TOA不发生时进入俯仰搜索阶段执行锁孔，并且其中航天器围绕偏航旋转 轴，停止，四元数复位，并且当从第二狭缝太阳传感器发生第二TOA时进入太阳保持相位。 最后，该方法包括太阳保持阶段，其中航天器被定向到太阳并以功率安全的姿态旋转。

公开(公告)号：US20030006345A1

公开(公告)日：2003-01-09

申请号：US10129160

申请日：2002-05-01

发明人： Yanping Guo

IPC分类号： B64G001/36

CPC分类号： G01C21/24 ,  B64G1/242 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365 ,  B64G1/366 ,  G01C21/025 ,  G01S3/7862 ,  G01S11/12 ,  G05D1/0883

摘要： A method and apparatus for autonomous navigation for deep space missions using the sun as the reference body and determining the spacecraft orbit based on observations made on the sun using onboard instruments. Two types of observation data, the direction of the spacecraft relative to the sun as a function of time and the optical Doppler shift due to the motion of the spacecraft relative to the sun, can be used for the spacecraft orbit determination. A dual imaging system which functions as a sun imager taking images of the sun against star backgrounds during the cruise phase and as a regular optical imager taking pictures of the targeting planetary body during the approaching phase is also described.

摘要翻译： 一种用于使用太阳作为参考体的深空任务的自主导航的方法和装置，并且基于使用车载仪器在太阳上观察来确定航天器轨道。 两种观测数据，航天器相对于太阳的方向作为时间的函数以及由于航天器相对于太阳的运动引起的光学多普勒频移可用于航天器的轨道确定。 还描述了作为太阳照相机的双重成像系统，其在巡航阶段期间拍摄太阳与星形背景的图像，并且作为在接近阶段期间拍摄目标行星体的常规光学成像仪也被描述。

公开(公告)号：US06441776B1

公开(公告)日：2002-08-27

申请号：US09479701

申请日：2000-01-07

申请人： Douglas H. Hein ,  Rongsheng Li

发明人： Douglas H. Hein ,  Rongsheng Li

IPC分类号： G01S502

CPC分类号： B64G1/242 ,  B64G1/24 ,  B64G1/26 ,  B64G1/288 ,  B64G1/36 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365 ,  B64G2001/245 ,  G01S19/53

摘要： A method, apparatus, and article of manufacture for directing a payload coupled to a spacecraft substantially at a target location is disclosed. The method comprises the steps of determining spacecraft orbital parameters and spacecraft payload attitude parameters; and directing the payload at the target location by applying a spacecraft bus steering law determined at least in part from the orbit and attitude parameters. The apparatus comprises a navigation system for determining spacecraft orbit parameters and spacecraft attitude parameters, and for applying a spacecraft bus steering law to direct the payload substantially at the target location. The spacecraft bus steering law is determined at least in part from the determined spacecraft orbital parameters, the determined spacecraft attitude, and determined payload attitude parameters. In one embodiment, the apparatus includes a payload attitude control system for directing the payload relative to the spacecraft bus. The article of manufacture comprises a program storage device tangibly embodying a series of instruction for performing the above method steps.

摘要翻译： 公开了一种用于引导耦合到航天器的有效载荷基本上在目标位置处的方法，装置和制品。 该方法包括确定航天器轨道参数和航天器有效载荷姿态参数的步骤; 以及通过应用至少部分地从轨道和姿态参数确定的航天器总线导向法，将有效载荷指向目标位置。 该装置包括用于确定航天器轨道参数和航天器姿态参数的导航系统，以及用于应用航天器总线指导规则以将有效载荷基本上引导到目标位置。 至少部分地根据确定的航天器轨道参数，确定的航天器姿态和确定的有效载荷姿态参数来确定航天器总线导向规律。 在一个实施例中，该装置包括用于将有效载荷相对于航天器总线引导的载荷姿态控制系统。 该制品包括有形地体现用于执行上述方法步骤的一系列指令的程序存储装置。

公开(公告)号：US06341249B1

公开(公告)日：2002-01-22

申请号：US09500530

申请日：2000-02-09

申请人： Guang Qian Xing ,  Shabbir Ahmed Parvez

发明人： Guang Qian Xing ,  Shabbir Ahmed Parvez

IPC分类号： B64G124

CPC分类号： B64G1/24 ,  B64G1/1085 ,  B64G1/242 ,  B64G1/26 ,  B64G1/283 ,  B64G1/285 ,  B64G1/288 ,  B64G1/32 ,  B64G1/36 ,  B64G1/361 ,  B64G1/363 ,  B64G1/365 ,  G05D1/0883

摘要： An apparatus and method of unified orbit and attitude control for acquisition and maintenance techniques of multiple satellites in a formation based on GPS input, utilizing Modern Feedback Control for providing precise autonomous on-board orbit and attitude control. This control system can place and maintain any satellite in its designated location in a formation, while simultaneously providing the capability to attain and maintain the attitude of any of the satellites in the formation with respect to the reference ‘head-of-fleet’ satellite. Utilizing the two different options of GPS signal, code pseudo range for orbit determination and control and phase pseudorange for attitude determination and control, the relative orbit and attitude state vectors of all the satellites in the formation is determined and modern advanced multivariable feedback control techniques, for example, linear quadratic Gaussian/loop transfer recovery controllers for orbit control and Sliding Controller or Lyapunov Controller for attitude control are used to provide a unified orbit and attitude control. The control of acquisition and maintenance for multiple spacecraft formation flying is a tracking problem, which can be converted into a regulator problem using the relative orbit and relative attitude kinematics and dynamics.

摘要翻译： 基于GPS输入的地层多卫星采集和维护技术的统一轨道和姿态控制的装置和方法，利用现代反馈控制提供精确的自主车载轨道和姿态控制。 该控制系统可以将任何卫星放置和维持在地层中的指定位置，同时提供相对于参考“舰长”卫星获得和维持地层中任何卫星的姿态的能力。 利用GPS信号的两个不同选项，用于姿态确定和控制的轨道确定和控制的伪伪距和相位伪距，确定了地层中所有卫星的相对轨道和姿态状态向量，并采用现代先进的多变量反馈控制技术， 例如，用于轨道控制的线性二次高斯/环路传输恢复控制器和用于姿态控制的滑模控制器或Lyapunov控制器用于提供统一的轨道和姿态控制，多个航天器形成飞行的采集和维护控制是一个跟踪问题， 这可以使用相对转换成调节器问题 轨道和相对姿态运动学和动力学。