公开(公告)号：US6138953A

公开(公告)日：2000-10-31

申请号：US33562

申请日：1998-03-02

申请人： Richard A. Noyola ,  Che-Hang C. Ih

发明人： Richard A. Noyola ,  Che-Hang C. Ih

IPC分类号： B64G1/24 ,  B64G1/28 ,  B64G1/36

CPC分类号： B64G1/285 ,  B64G1/24 ,  B64G1/283 ,  B64G2001/247

摘要： Autonomous slewing of a spacecraft about a desired axis using reaction wheels permits a maximum slew rate without wheel saturation even with one wheel failure. The slew is carried out if the total angular momentum of the spacecraft is less than a momentum storage threshold determined from reaction wheel availability. The momentum threshold may be found as the radius of a sphere inscribed in a polyhedron in momentum space, the polyhedron based on the maximum single wheel capacity and the geometry of the reaction wheel system as well as the reaction wheel availability. The momentum available for the slew is determined from the total angular momentum and the availability of each reaction wheel. The slew rate magnitude and slew direction are based on the available momentum. The available momentum calculation may include factors to accommodate noise and model uncertainties, to prevent the slew from placing the total angular momentum into a state overly limiting the rate of a subsequent slew, and to avoid numerical problems.

摘要翻译： 使用反作用轮自动回转航天器绕期望的轴，即使在一个车轮故障的情况下也能实现无砂轮饱和的最大转换速率。 如果航天器的总角动量小于从反作用轮可用性确定的动量存储阈值，则进行转换。 动量阈值可以被发现为在动量空间中刻写在多面体中的球的半径，多面体基于最大单轮容量和反作用轮系统的几何形状以及反作用轮的可用性。 可用于转速的动量由总角动量和每个反作用轮的可用性确定。 压摆率和转换方向取决于可用的动量。 可用的动量计算可以包括适应噪声和模型不确定性的因素，以防止转矩将总角动量置于过度限制后续转矩速率的状态中，并避免数字问题。

公开(公告)号：US07025307B2

公开(公告)日：2006-04-11

申请号：US10318715

申请日：2002-12-13

申请人： Hanching Grant Wang ,  Richard A. Fowell ,  Che-Hang C. Ih

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

IPC分类号： E03H5/00

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：US07337097B2

公开(公告)日：2008-02-26

申请号：US10804549

申请日：2004-03-18

申请人： Che-Hang C. Ih

发明人： Che-Hang C. Ih

IPC分类号： G06F7/60 ,  G06F17/00 ,  B64G1/36

CPC分类号： G06F17/5009 ,  G06F17/5095 ,  H01Q1/288 ,  H01Q15/161 ,  H01Q15/168

摘要： A method for modeling a structure deployed on a spacecraft. The method includes determining a geometric shape that resembles the structure in a fully deployed configuration; generating time functions for a change in shape of at least one structural component of the structure, the change in shape occurring as the structure expands into the fully deployed configuration; and calculating mass properties of the geometric shape as a function of the time functions.

摘要翻译： 一种对部署在航天器上的结构进行建模的方法。 该方法包括确定类似于完全展开配置中的结构的几何形状; 产生用于结构的至少一个结构部件的形状变化的时间功能，随着结构扩展到完全展开的构型，形状发生变化; 并计算几何形状的质量属性作为时间函数的函数。

公开(公告)号：US06990396B2

公开(公告)日：2006-01-24

申请号：US10318867

申请日：2002-12-13

申请人： Hanching Grant Wang ,  Richard A. Fowell ,  Che-Hang C. Ih

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

IPC分类号： G06F7/00

CPC分类号： B64G1/24 ,  B64G1/26 ,  B64G1/281 ,  B64G1/283 ,  B64G1/285 ,  B64G1/288 ,  B64G1/361 ,  B64G1/363 ,  B64G1/366

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 comprises the steps of predicting an environmental torque the spacecraft will be subjected to during deployment of the appendage, computing a magnitude and a direction of momentum to add to the spacecraft to at least partially oppose the predicted environmental torque, and storing the computed magnitude and direction of momentum in at least one of the momentum wheels before deploying the appendage.

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。 该方法包括以下步骤：在部署附件期间预测航天器将遭受的环境扭矩，计算增加到航天器的动量的大小和方向以至少部分地反对预测的环境转矩，并且存储所计算的大小 并且在部署附件之前至少有一个动量轮的动量方向。

公开(公告)号：US06089508A

公开(公告)日：2000-07-18

申请号：US33561

申请日：1998-03-02

申请人： Richard A. Noyola ,  Che-Hang C. Ih

发明人： Richard A. Noyola ,  Che-Hang C. Ih

IPC分类号： B64G1/28 ,  B64G1/36 ,  G05D1/08

CPC分类号： G05D1/0883 ,  B64G1/283 ,  B64G1/288 ,  B64G1/363 ,  B64G2001/247

摘要： A spacecraft with a reaction wheel system can be autonomously safed by setting the solar wings to continuous tracking, determining a slew rate vector based on the total angular momentum, and slewing the spacecraft using the slew rate vector until commanded to stop autonomous safing. In a typical application, the spacecraft has a reaction wheel assembly with four wheels arranged to form a right regular pyramid. Two reaction wheels on opposite edges of the pyramid form a first pair and the two remaining reaction wheels forming a second pair. The slew axis of rotation is found by determining as a selected pair the first pair if either reaction wheel in the second pair is inoperative, otherwise determining as the selected pair the second pair and determining as the slew axis of rotation the normalized projection of the axes of rotation of the selected pair onto the base. The slew direction is determined by the sign of the total angular momentum component along the slew axis of rotation.

摘要翻译： 具有反作用系统的航天器可以通过将太阳翼设置为连续跟踪，基于总角动量确定转换速率向量，以及使用转换速率向量旋转航天器直到命令停止自主安全，自主安全。 在典型的应用中，航天器具有一个具有四个轮子的反作用轮组件，以便形成一个正规的金字塔。 金字塔的相对边缘上的两个反作用轮形成第一对，并且剩下的两个反作用轮形成第二对。 如果第二对中的任一个反作用轮不起作用，则确定作为选定对的第一对，否则将第二对确定为所选择的对，并将其确定为旋转轴的旋转轴的标准化投影 所选择的对旋转到基座上。 转动方向由绕旋转轴旋转的总角动量分量的符号决定。