公开(公告)号：US20150375876A1

公开(公告)日：2015-12-31

申请号：US14120788

申请日：2014-06-27

Applicant: Darren D. Garber

Inventor： Darren D. Garber

IPC: B64G1/66 ,  H03K3/01 ,  B64G1/26 ,  B64G1/36 ,  B64G1/10 ,  B64G1/22

CPC classification number: B64G1/66 ,  B64G1/10 ,  B64G1/1085 ,  B64G1/222 ,  B64G1/242 ,  B64G1/26 ,  B64G1/36 ,  B64G1/361 ,  B64G1/64 ,  B64G1/648 ,  B64G3/00

Abstract: A spacecraft arrangement having sensors for providing the three dimensional imaging of space object to be imaged and having a plurality of spaced apart nodes defining an open imaging area therebetween through which imaging area the space object to be imaged passes.

Abstract translation: 具有用于提供要成像的空间物体的三维成像并具有多个间隔开的节点的传感器的航天器装置，所述多个间隔开的节点限定其间的开放成像区域，成像空间物体通过该成像区域通过。

公开(公告)号：US20150367966A1

公开(公告)日：2015-12-24

申请号：US14745875

申请日：2015-06-22

Applicant: Los Alamos National Security, LLC

Inventor： Stephen Judd ,  Nicholas Dallmann ,  Michael Proicou ,  Daniel Seitz ,  Paul Stein ,  John Martinez ,  Gayle Kestell ,  Adam Warniment ,  Steven Storms

IPC: B64G1/36 ,  B64G1/28 ,  G05D1/08

CPC classification number: B64G1/363 ,  B64G1/244 ,  B64G1/283 ,  B64G1/361

Abstract: An ADCS module may be configured to use coordinate data from 2D photodiodes in one or more sun sensors to determine a sun vector. The ADCS module may then use the sun vector in reference to its own body faced (BF) coordinate system to calculate a change in the orientation of the space vehicle. The change in orientation mechanism may be accomplished by reaction wheels, ion thrusters, or other orientation altering mechanisms. A miniature, intelligent star tracker may be included that improves satellite attitude determination and pointing accuracy. An improved reaction wheel assembly may be included that is more robust and suitable for inclusion in small space vehicles.

Abstract translation: ADCS模块可以被配置为在一个或多个太阳传感器中使用来自2D光电二极管的坐标数据来确定太阳矢量。 然后，ADCS模块可以参考其自身的身体（BF）坐标系来使用太阳矢量来计算空间车辆的取向的变化。 取向机构的变化可以通过反作用轮，离子推进器或其它取向改变机构来实现。 可以包括一种微型智能星形跟踪器，可以改善卫星姿态确定和指向精度。 可以包括改进的反作用轮组件，其更加坚固并且适合于包含在小型空间车辆中。

公开(公告)号：US09217643B1

公开(公告)日：2015-12-22

申请号：US14121918

申请日：2014-11-03

Applicant: Mikhail S. Belenkii ,  Timothy Brinkley

Inventor： Mikhail S. Belenkii ,  Timothy Brinkley

IPC: G01C21/10 ,  G01C21/02 ,  G01C21/18 ,  G01S19/40 ,  G01C21/16 ,  G01S19/47 ,  G01S5/16 ,  B64G1/36 ,  G01C15/00 ,  B64G1/24 ,  G05D1/08

CPC classification number: G01C21/025 ,  B64G1/24 ,  B64G1/36 ,  G01C15/00 ,  G01C15/002 ,  G01C21/10 ,  G01C21/165 ,  G01C21/18 ,  G01C25/005 ,  G01S5/16 ,  G01S19/40 ,  G01S19/47 ,  G05D1/0883

Abstract: An angles only navigation system. The system includes an IMU coupled with a passive optical sensor. The optical sensor provides periodic updates to the IMU in order to correct for accelerometer and gyro drifts. The IMU computes the air vehicle's instantaneous position, velocity, and attitude using gyro and accelerometer measurements. The optical sensor images stars and satellites. The navigation filter combines optical sensor measurements with IMU inputs, and determines those corrections needed to compensate for the IMU drifts. By applying periodic corrections to the IMU using satellite angular measurements, the navigation filter maintains an accurate position estimate during an entire flight.

Abstract translation: 一个角度只有导航系统。 该系统包括与无源光学传感器耦合的IMU。 光学传感器为IMU提供定期更新，以校正加速度计和陀螺仪漂移。 使用陀螺仪和加速度计测量，IMU计算飞行器的瞬时位置，速度和姿态。 光学传感器图像星星和卫星。 导航滤波器将光学传感器测量与IMU输入相结合，并确定补偿IMU漂移所需的校正。 通过使用卫星角度测量对IMU进行周期性校正，导航滤波器在整个飞行期间保持准确的位置估计。

公开(公告)号：US09045241B2

公开(公告)日：2015-06-02

申请号：US13945821

申请日：2013-07-18

Applicant: Thales

Inventor： François Caullier ,  Faustine Delhay ,  Jean-Marc Lacambre ,  Etienne Brouillard

IPC: B64G1/00 ,  B64G1/28 ,  B64G1/24 ,  B64G1/26 ,  B64G1/36 ,  G05D1/08

CPC classification number: 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

Abstract: 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.

Abstract translation: 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转矩; 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。

公开(公告)号：US20150100272A1

公开(公告)日：2015-04-09

申请号：US14341159

申请日：2014-07-25

Applicant: Andrew C. Nicholas ,  Nelson Creamer ,  Theodore T. Finne ,  Federico A. Herrero

Inventor： Andrew C. Nicholas ,  Nelson Creamer ,  Theodore T. Finne ,  Federico A. Herrero

IPC: B64G1/36 ,  B64G1/10

CPC classification number: B64G1/366 ,  B64G1/36

Abstract: A method and system is described for determining attitude for a satellite. A two-axis ram sensor head measures neutral winds and provides a density of the neutral winds. A three-axis magnetometer measures a geomagnetic field. A measurement interface module calculates attitude information, which includes three-axis attitude knowledge of a satellite relative to a local-vertical local-horizontal orbit frame, based on the combined ram measurements and magnetic field measurements, and provides the attitude information to a satellite that comprises the attitude sensor system.

Abstract translation: 描述了一种用于确定卫星姿态的方法和系统。 两轴柱塞传感器头测量中性风，并提供中性风的密度。 三轴磁力计测量地磁场。 测量接口模块基于组合的拉杆测量和磁场测量来计算姿态信息，其包括卫星相对于局部 - 垂直局部 - 水平轨道帧的三轴姿态知识，并且向卫星提供姿态信息 包括姿态传感器系统。

公开(公告)号：US20150041595A1

公开(公告)日：2015-02-12

申请号：US14454162

申请日：2014-08-07

Applicant: Jena Optronik GmbH

Inventor： Rolf Hartmann ,  Dieter Schoedlbauer ,  Uwe Schmidt

IPC: B64G1/36 ,  B64G1/24 ,  B64G1/10

CPC classification number: B64G1/361 ,  B64G1/10 ,  B64G1/242 ,  B64G1/288 ,  B64G1/36 ,  G01C21/025

Abstract: A hybrid network of kinematic sensors of an AOCS, made up of a star sensor including an optical camera head, and a processing unit provided as the central master processing unit, and additional kinematic sensors, each made up of a sensor element and a processing unit connected to the central processing unit via a first bus. An additional processing unit is equivalent to the processing unit and is a redundant central processing unit. The central processing units and—are connected via an additional bus of a spacecraft provided with the hybrid network with the aid of a central computer. The particular active central processing units-provide all kinematic sensors with a uniform time pulse via a synchronization line, and supply the central computer with hybridized kinematic measuring data formed according to a method for hybridization based on the synchronous kinematic measuring data of the star sensor and the measuring data of the other sensors.

Abstract translation: AOCS的运动学传感器的混合网络由包括光学相机头的星形传感器和作为中央主处理单元提供的处理单元组成，并且每个由传感器元件和处理单元组成的附加运动传感器 通过第一总线连接到中央处理单元。 附加处理单元等同于处理单元，并且是冗余中央处理单元。 中央处理单元通过中央计算机的辅助，通过配有混合网络的航天器的附加总线相连接。 特定的活动中央处理单元 - 通过同步线为所有运动传感器提供均匀的时间脉冲，并且基于星传感器的同步运动测量数据，根据用于杂交的方法形成的混合运动学测量数据提供给中央计算机; 其他传感器的测量数据。

公开(公告)号：US20140231589A1

公开(公告)日：2014-08-21

申请号：US14181492

申请日：2014-02-14

Applicant: The Boeing Company

Inventor： Tung-Ching Tsao ,  Richard Y. Chiang

IPC: B64G1/36 ,  B64G1/44 ,  B64G3/00

CPC classification number: B64G1/363

Abstract: An attitude estimator that uses sun sensor outputs as the only attitude determination measurements to provide three-axis attitude information. This is accomplished by incorporating the Euler equation into the estimator. An unscented Kalman filter is employed to accommodate various nonlinear characteristics and uncertainties of the spacecraft dynamics and thus improve the robustness and accuracy of the attitude estimate.

Abstract translation: 使用太阳传感器输出作为唯一姿态确定测量来提供三轴姿态信息的姿态估计器。 这通过将欧拉方程并入估计器来实现。 采用无色卡尔曼滤波器来适应航天器动力学的各种非线性特征和不确定性，从而提高姿态估计的鲁棒性和准确性。

公开(公告)号：US08550405B2

公开(公告)日：2013-10-08

申请号：US12807222

申请日：2010-08-31

Applicant: Vladimir Hruby ,  Thomas Jaquish ,  Antonio Rizzo ,  Eric Ehrbar

Inventor： Vladimir Hruby ,  Thomas Jaquish ,  Antonio Rizzo ,  Eric Ehrbar

IPC: B64G1/36

CPC classification number: B64G1/405 ,  B64G1/425 ,  B64G1/428 ,  B64G1/44 ,  F03H1/0018

Abstract: A solar powered spacecraft power system including a solar photovoltaic array, an electric propulsion system connected directly to the solar photovoltaic array in parallel with the spacecraft power system; the electric propulsion system including a Hall effect thruster, a thruster power supply for driving the thruster; a sensor for sensing the power output of the solar array and a controller responsive to the power output of the solar array and configured to periodically adjust an operating parameter of the thruster to operate the thruster at the maximum available output power of the solar array including comparing a previous solar array output power level with a later solar array output power level, and incrementing the operating parameter with a positive value if the later is greater and with a negative value if the later is lesser; a solar powered spacecraft power system including a solar photovoltaic array, an electric propulsion system connected directly to the solar photovoltaic array, and a power management and distribution system connected to the solar photovoltaic array for distributing power to one or more bus loads and payloads.

Abstract translation: 一种太阳能航天器电力系统，包括太阳能光伏阵列，与太阳能光伏阵列直接连接的电力推进系统，与太空电力系统平行; 电动推进系统包括霍尔效应推进器，用于驱动推进器的推进器电源; 用于感测太阳能阵列的功率输出的传感器和响应于太阳能阵列的功率输出的控制器，并且被配置为周期性地调整推进器的操作参数以在太阳能阵列的最大可用输出功率下操作推进器，包括比较 以前的太阳能阵列输出功率电平，具有稍后的太阳能阵列输出功率电平，并且如果后者较大则增加具有正值的运行参数，并且如果稍后较小则增加负值; 包括太阳能光伏阵列，直接连接到太阳能光伏阵列的电力推进系统的太阳能航天器电力系统，以及连接到太阳能光伏阵列以将功率分配给一个或多个总线负载和有效载荷的电力管理和分配系统。

公开(公告)号：US08437892B1

公开(公告)日：2013-05-07

申请号：US13010202

申请日：2011-01-20

Applicant: Alan Scott Hope ,  Annie Megan Lum

Inventor： Alan Scott Hope ,  Annie Megan Lum

IPC: B64G1/36

CPC classification number: B64G1/242 ,  B64G1/1085 ,  B64G1/36

Abstract: A method of establishing a formation of a plurality of directionally fixed satellites, such as primary formation of the satellites with in-track velocity disparity. The plurality of satellites includes an anchor satellite and at least one non-anchor satellite, each satellite of the plurality of satellites including at least one drag flap, each satellite of the plurality of satellites being free of one of a propulsion system and an expendable mass propellant. Control is applied to deploy the at least one drag flap of the at least one non-anchor satellite based on the current spacing and the current separation rate of the each non-anchor satellite, and the predicted final spacing of the plurality of satellites. The final spacing predicting and the drag flap control applying is repeated until the current separation rate has been nulled to within a threshold value.

Abstract translation: 建立多个定向固定卫星的形成的方法，例如具有轨道内速度差异的卫星的初步形成。 所述多个卫星包括锚卫星和至少一个非锚卫星，所述多个卫星中的每颗卫星包括至少一个拖曳翼片，所述多颗卫星中的每颗卫星不含推进系统和消耗质量块之一 推进剂。 基于当前间隔和每个非锚定卫星的当前分离速率以及多个卫星的预测的最终间距来应用控制来部署至少一个非锚定卫星的至少一个拖曳翼片。 重复最终间距预测和拖曳襟翼控制应用，直到目前的分离速率已经被置零到阈值内。

公开(公告)号：US20130085628A1

公开(公告)日：2013-04-04

申请号：US13251785

申请日：2011-10-03

Applicant: Rongsheng Li ,  Tung-Ching Tsao ,  Arunkumar P. Nayak

Inventor： Rongsheng Li ,  Tung-Ching Tsao ,  Arunkumar P. Nayak

IPC: B64G1/36 ,  G06F19/00 ,  G01C25/00

CPC classification number: G01C21/165 ,  G05D1/0883

Abstract: Methods, systems, and computer-readable media are described herein for using a modified Kalman filter to generate attitude error corrections. Attitude measurements are received from primary and secondary attitude sensors of a satellite or other spacecraft. Attitude error correction values for the attitude measurements from the primary attitude sensors are calculated based on the attitude measurements from the secondary attitude sensors using expanded equations derived for a subset of a plurality of block sub-matrices partitioned from the matrices of a Kalman filter, with the remaining of the plurality of block sub-matrices being pre-calculated and programmed into a flight computer of the spacecraft. The propagation of covariance is accomplished via a single step execution of the method irrespective of the secondary attitude sensor measurement period.

Abstract translation: 本文描述了使用修改的卡尔曼滤波器来产生姿态误差校正的方法，系统和计算机可读介质。 从卫星或其他航天器的主要和次要姿态传感器接收姿态测量。 基于来自二级姿态传感器的姿态测量，使用从卡尔曼滤波器的矩阵分割的多个块子矩阵的子集导出的扩展方程式来计算来自主姿态传感器的姿态测量值的姿态误差校正值， 多个块子矩阵的剩余部分被预先计算并编程到航天器的飞行计算机中。 无论二次姿态传感器测量周期如何，通过该方法的单步执行来实现协方差的传播。