公开(公告)号：US20140027576A1

公开(公告)日：2014-01-30

申请号：US13949861

申请日：2013-07-24

申请人： Christopher Boshuizen ,  William Marshall ,  James Mason ,  Robert Schingler, JR.

发明人： Christopher Boshuizen ,  William Marshall ,  James Mason ,  Robert Schingler, JR.

IPC分类号： B64G1/10

CPC分类号： B64G1/1085 ,  B64G2001/1028 ,  B64G2001/245

摘要： The focus of this invention pertains to the methodology behind launching line-scanning satellite constellations that can image an entire planet such as the Earth at high temporal cadence (less than a week), at high spatial resolution (less than 10 m). Utilizing simple control and operation, our invention captures images of an entire planet in an effective and distributed manner. Additional benefits are realized by taking advantage of the distributed onboard storage and computing abilities of such a constellation to optimize the data collected, system latency, and data downlinked.

摘要翻译： 本发明的重点涉及发射线扫描卫星星座的方法，其可以以高空间分辨率（小于10m）以高时间节奏（少于一周）对整个行星，例如地球进行成像。 利用简单的控制和操作，我们的发明以有效和分布的方式捕获整个地球的图像。 通过利用这种星座的分布式板载存储和计算能力来优化收集的数据，系统延迟和下行数据来实现额外的益处。

公开(公告)号：US08612068B2

公开(公告)日：2013-12-17

申请号：US13198598

申请日：2011-08-04

申请人： Russell P Patera

发明人： Russell P Patera

IPC分类号： G05D1/00 ,  G05D1/08 ,  G05D3/00 ,  G06F17/00

CPC分类号： G01C21/24 ,  B64G1/24 ,  B64G1/36 ,  B64G2001/245 ,  G01C21/16

摘要： Apparatus and method is provided for propagating the attitude of a vehicle. A slew rate is computed based on angular rotation increments associated with a time interval. An incremental update is computed for the associated time interval based on an angular rate and the slew rate. An attitude of the vehicle is propagated based on the computed attitude increment and an initial attitude at the start of propagation.

摘要翻译： 提供了用于传播车辆姿态的装置和方法。 基于与时间间隔相关联的角度旋转增量来计算压摆率。 基于角速率和转换速率计算相关时间间隔的增量更新。 基于计算出的姿态增量和在开始传播时的初始姿态来传播车辆的姿态。

公开(公告)号：US08571727B1

公开(公告)日：2013-10-29

申请号：US13760189

申请日：2013-02-06

申请人： The Aerospace Corporation

发明人： Russell Paul Patera

IPC分类号： B64G1/24

CPC分类号： B64G1/002 ,  B64G2001/245 ,  G05D1/0883

摘要： An improved method for launch vehicle guidance is disclosed. A pre-computed energy-angular momentum (E-J) curve to place a launch vehicle into a target orbit is received and stored. An energy, angular momentum, radial distance, velocity magnitude, and flight path angle of the launch vehicle are computed from state vector data while the launch vehicle is traveling to the target orbit. The pre-computed E-J curve and the computed energy, angular momentum, radial distance, velocity magnitude, and flight path angle of the launch vehicle are used to determine pitch and pitch rate of the launch vehicle.

摘要翻译： 公开了一种改进的运载火箭引导方法。 接收并存储将运载火箭放置到目标轨道中的预计算能量角动量（E-J）曲线。 当运载火箭运行到目标轨道时，从状态向量数据计算运载火箭的能量，角动量，径向距离，速度幅度和飞行路径角度。 使用预计算的E-J曲线和运载火箭的计算能量，角动量，径向距离，速度幅度和飞行路径角度来确定运载火箭的俯仰和俯仰速率。

公开(公告)号：US08380370B2

公开(公告)日：2013-02-19

申请号：US12487187

申请日：2009-06-18

申请人： Dan Y. Liu ,  Richard Y. Chiang

发明人： Dan Y. Liu ,  Richard Y. Chiang

IPC分类号： B64G1/24

CPC分类号： B64G1/26 ,  B64G1/283 ,  B64G1/36 ,  B64G1/361 ,  B64G2001/245 ,  G05D1/0883

摘要： A system and a method for commanding a spacecraft to perform a three-axis maneuver purely based on “position” (i.e., attitude) measurements. Using an “inertial gimbal concept”, a set of formulae are derived that can map a set of “inertial” motion to the spacecraft body frame based on position information so that the spacecraft can perform/follow according to the desired inertial position maneuvers commands. Also, the system and method disclosed herein employ an intrusion steering law to protect the spacecraft from acquisition failure when a long sensor intrusion occurs.

摘要翻译： 一种用于命令航天器完全基于位置（即姿态）测量进行三轴机动的系统和方法。 使用惯性万向节概念，导出一组公式，其可以基于位置信息将一组惯性运动映射到航天器身体框架，使得航天器可以根据期望的惯性姿态操纵命令执行/跟随。 此外，本文公开的系统和方法采用入侵转向规律来保护航天器在发生长传感器入侵时不会获取故障。

公开(公告)号：US20130035803A1

公开(公告)日：2013-02-07

申请号：US13198598

申请日：2011-08-04

申请人： RUSSELL P. PATERA

发明人： RUSSELL P. PATERA

IPC分类号： G05D1/00

CPC分类号： G01C21/24 ,  B64G1/24 ,  B64G1/36 ,  B64G2001/245 ,  G01C21/16

摘要： Apparatus and method is provided for propagating the attitude of a vehicle. A slew rate is computed based on angular rotation increments associated with a time interval. An incremental update is computed for the associated time interval based on an angular rate and the slew rate. An attitude of the vehicle is propagated based on the computed attitude increment and an initial attitude at the start of propagation.

摘要翻译： 提供了用于传播车辆姿态的装置和方法。 基于与时间间隔相关联的角度旋转增量来计算压摆率。 基于角速率和转换速率计算相关时间间隔的增量更新。 基于计算出的姿态增量和在开始传播时的初始姿态来传播车辆的姿态。

公开(公告)号：US20120053780A1

公开(公告)日：2012-03-01

申请号：US12946882

申请日：2010-11-16

申请人： Chan Gook PARK ,  Jun Han LEE ,  Won Hee LEE

发明人： Chan Gook PARK ,  Jun Han LEE ,  Won Hee LEE

IPC分类号： G06F19/00 ,  G01M17/00

CPC分类号： B64G1/24 ,  B64G1/26 ,  B64G1/283 ,  B64G2001/245

摘要： Provided are a fault detector and a fault detection method for an attitude control system (ACS) of a spacecraft. The fault detector includes a first interacting multiple model (IMM) fault detection block for generating a normal model filter of the plurality of actuators and a plurality of upper level filters including fault model filters corresponding to the respective actuators, and detecting faults of the plurality of actuators using an IMM estimation technique from the plurality of upper level filters, and a second IMM fault detection block for generating a plurality of lower level filters each including a fault type model filter of the fault-detected actuator in the first IMM fault detection block, and detecting a fault type of the failed actuator using the IMM estimation technique.

摘要翻译： 提供了一种用于航天器的姿态控制系统（ACS）的故障检测器和故障检测方法。 故障检测器包括用于产生多个致动器的正常模型滤波器的第一交互多模型（IMM）故障检测块和包括与各个致动器相对应的故障模型滤波器的多个上级滤波器，并且检测多个 执行器，其使用来自多个上级滤波器的IMM估计技术;以及第二IMM故障检测块，用于生成多个下级滤波器，每个低电平滤波器包括第一IMM故障检测块中的故障检测致动器的故障型模型滤波器， 并使用IMM估计技术检测故障致动器的故障类型。

公开(公告)号：US07805226B2

公开(公告)日：2010-09-28

申请号：US11540452

申请日：2006-09-29

申请人： Brian J. Hamilton ,  Brian K. Underhill

发明人： Brian J. Hamilton ,  Brian K. Underhill

IPC分类号： B64G1/36

CPC分类号： B64G1/286 ,  B64G2001/245 ,  G05D1/0883 ,  Y10T74/12 ,  Y10T74/1221 ,  Y10T74/1229

摘要： A control system for adjusting the attitude of a spacecraft comprises a set of control moment gyroscopes (CMGs) configured to allow null space maneuvering. The control system further comprises a momentum actuator control processor coupled to the set of CMGs and configured to determine a mandatory null space maneuver to avoid singularities and determine an optional null space maneuver to increase available torque. The mandatory null space maneuver can be calculated based upon certain gimbal angles, and can be implemented by augmenting the inverse-Jacobian control matrix.

摘要翻译： 用于调节航天器姿态的控制系统包括一组配置成允许空间空间操纵的控制力矩陀螺仪（CMG）。 控制系统还包括耦合到该组CMG的动量致动器控制处理器，并且被配置为确定强制性零空间操纵以避免奇点并且确定可选的零空间机动以增加可用转矩。 可以基于某些万向节角度来计算强制空间机动，并且可以通过增加逆雅可比控制矩阵来实现。

公开(公告)号：US20100193641A1

公开(公告)日：2010-08-05

申请号：US12487187

申请日：2009-06-18

申请人： Dan Y. Liu ,  Richard Y. Chiang

发明人： Dan Y. Liu ,  Richard Y. Chiang

IPC分类号： B64G1/36 ,  B64G1/26 ,  B64G1/24

CPC分类号： B64G1/26 ,  B64G1/283 ,  B64G1/36 ,  B64G1/361 ,  B64G2001/245 ,  G05D1/0883

摘要： A system and a method for commanding a spacecraft to perform a three-axis maneuver purely based on “position” (i.e., attitude) measurements. Using an “inertial gimbal concept”, a set of formulae are derived that can map a set of “inertial” motion to the spacecraft body frame based on position information so that the spacecraft can perform/follow according to the desired inertial position maneuvers commands. Also, the system and method disclosed herein employ an intrusion steering law to protect the spacecraft from acquisition failure when a long sensor intrusion occurs.

摘要翻译： 用于命令航天器完全基于“位置”（即姿态）测量执行三轴机动的系统和方法。 使用“惯性万向节概念”，导出一组公式，其可以基于位置信息将一组“惯性”运动映射到航天器身体框架，使得航天器可以根据期望的惯性姿态操纵命令执行/跟随。 此外，本文公开的系统和方法采用入侵转向规律来保护航天器在发生长传感器入侵时不会获取故障。

公开(公告)号：US20060049315A1

公开(公告)日：2006-03-09

申请号：US10522576

申请日：2004-10-14

申请人： Moonish Patel ,  Neil Goodzeit

发明人： Moonish Patel ,  Neil Goodzeit

IPC分类号： B64G1/26

CPC分类号： B64G1/283 ,  B64G1/007 ,  B64G1/26 ,  B64G2001/245

摘要： A system for providing attitude control with respect to a spacecraft is provided. The system includes a reaction wheel control module configured to control a number of reaction wheel assemblies associated with the spacecraft in order to control attitude, and a maneuver control module configured to use a number of gimbaled Hall Current thrusters (HCTs) to control the total momentum associated with the spacecraft during an orbit transfer. The total momentum includes the momentum associated with the reaction wheel assemblies and the angular momentum of the spacecraft. Using the gimbaled HCTs to control the momentum associated with the reaction wheel assemblies during the orbit transfer results in minimal HCT gimbal stepping.

摘要翻译： 提供了一种用于提供关于航天器的姿态控制的系统。 该系统包括反作用轮控制模块，其配置成控制与航天器相关联的多个反作用轮组件以控制姿态;以及机动控制模块，其被配置为使用多个万向霍尔电流推进器（HCT）来控制总动量 在轨道转移期间与航天器相关联。 总动量包括与反作用轮组件相关的动量和航天器的角动量。 在轨道转移期间使用万向HCT来控制与反作用轮组件相关的动量导致最小的HCT万向节步进。

公开(公告)号：US20050027407A1

公开(公告)日：2005-02-03

申请号：US10493611

申请日：2002-10-08

申请人： Anthony Holt ,  Michele Janvier

发明人： Anthony Holt ,  Michele Janvier

IPC分类号： B64G1/26 ,  B64G1/28 ,  B64G1/36 ,  B64G1/38 ,  G05D1/08 ,  G05D1/00

CPC分类号： B64G1/26 ,  B64G1/281 ,  B64G1/361 ,  B64G1/38 ,  B64G2001/245 ,  B64G2001/247 ,  G05D1/0883

摘要： An inventive autonomous active manoeuvring method and system 1 for spinning spacecraft is provided having a capability to enhance the AOCMS performance of passive spinning satellites and to fulfil the emerging autonomy requirements applicable to new generation satellites. In broad terms, the invention resides in (a) the overall concept of providing autonomous execution of spin axis re-orientation manoeuvring for spinning spacecraft designed and executed autonomously on-board the spacecraft by the AOCMS and (b) in the proposed strategy set in place to execute the re-orientation manoeuvres with respect to the handling of residual nutation. Advantageously, the provision of coupling nutation avoidance manoeuvres with active nutation damping 8 on board the spacecraft reduces/minimises the manoeuvre settling time required to return the spacecraft to the steady state pointing performance, while not imposing constraints upon the particular spacecraft inertia sensor properties.

摘要翻译： 提供了一种用于旋转航天器的创新的自主主动操纵方法和系统1，其具有增强被动旋转卫星的AOCMS性能并满足适用于新一代卫星的新兴自主性要求的能力。 广义而言，本发明在于（a）提供自主执行旋转轴重定向机动的总体概念，用于由AOCMS自主设计和执行航天器的飞行器的飞行器，以及（b）在所提出的策略集 处理剩余章动的地方进行重新定位。 有利的是，在航天器上提供具有主动式章动阻尼8的联动轮廓避免机动作用减少/最小化将飞船返回到稳态指向性能所需的机动稳定时间，同时不对特定的航天器惯性传感器特性施加约束。