公开(公告)号：EP1128247A2

公开(公告)日：2001-08-29

申请号：EP01301642.3

申请日：2001-02-23

申请人： Space Systems / Loral, Inc.

发明人： Holmes, Thomas J. ,  Cielaszyk, David

IPC分类号： G05D1/08

CPC分类号： G05D1/0883

摘要： Apparatus and a method is presented for controlling yaw and roll excursions in a spacecraft (20) having on-board components such as magnetic torquers (22,24), a roll thruster (32,34), momentum wheels (26,28,30), a wheel controller, an earth sensor, and a Digital Integrating Rate Assembly (DIRA). An observer module on the spacecraft receives inputs containing information comprising the unbiased roll error from the earth sensor, yaw momentum measured from the wheel speeds, and commanded yaw and pitch momentum output from the wheel controller, and produces therefrom output signals indicative of yaw estimate, yaw momentum estimate and torque disturbances estimate. A controller module on the spacecraft receives the output signals and combines them with inputs containing information comprising minimum yaw error and roll thrust yaw controller gain and minimum yaw error and roll thrust yaw momentum controller gain, and produces therefrom a signal for commanding the operation of the magnetic torquers to change roll momentum when within the dead band of the signal and, alternatively, for commanding the operation of both the magnetic torquers (22,24) and the roll thruster (32,34) to change roll momentum when the threshold of the dead band is exceeded. By so doing, the yaw attitude and yaw excursions are controlled.

摘要翻译： 提出了一种用于控制具有板载部件的航空器（20）中的偏航和滚动偏移的装置和方法，所述飞行器具有诸如磁性扭矩（22,24），滚动推进器（32,34），动量轮（26,28,30 ），车轮控制器，地球传感器和数字积分速率组件（DIRA）。 航天器上的观测器模块接收包含来自地球传感器的信息的信息的输入，从车轮速度测量的偏航动量以及从车轮控制器输出的命令的偏航和俯仰动量，并从其产生表示偏航估计的输出信号， 横摆动量估计和扭矩扰动估计。 航天器上的控制器模块接收输出信号，并将它们与包含包括最小偏航误差和侧倾推力偏航控制器增益以及最小偏航误差和侧倾推力偏航摇摆控制器增益的信息的输入组合，并由此产生用于命令操作的信号 当在信号的死区内改变滚动动量的磁性扭矩，或者当用于控制磁力扳机（22,24）和滚动推进器（32,34）的操作来改变滚动动量 超过死区。 通过这样做，控制偏航姿态和偏航偏移。

公开(公告)号：EP0853040A1

公开(公告)日：1998-07-15

申请号：EP97310195.9

申请日：1997-12-16

申请人： Space Systems/Loral, Inc.

发明人： Holmes, Thomas J. ,  Purvis, Christopher R.

IPC分类号： B64G1/26 ,  G05D1/08

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

摘要： A method for controlling the direction of a spacecraft (10), of the type having a controller (16) for calculating thrust forces. The method comprises the use of a plurality of thrusters (1, 2, 3, 4) disposed on the spacecraft in a spaced relationship relative to one another and aligning and locating each of the plurality of thrusters at a predetermined angle on the spacecraft relative to first, second and third orthogonally oriented axes (X, Y, Z) such that the firing of any given pair of thrusters (1, 2, 3, 4) produces a torque about one of the spacecraft axes (X, Y, Z).

摘要翻译： 一种用于控制航天器（10）的方向的方法，该方法具有用于计算推力的控制器（16）。 该方法包括使用以彼此间隔开的关系设置在航天器上的多个推进器（1,2,3,4），并且使所述多个推进器中的每一个以相对于 第一，第二和第三正交取向轴（X，Y，Z），使得任何给定的一对推进器（1,2,3,4）的点火产生围绕航天器轴线（X，Y，Z）之一的转矩， 。

公开(公告)号：EP1128247A3

公开(公告)日：2002-09-18

申请号：EP01301642.3

申请日：2001-02-23

申请人： Space Systems / Loral, Inc.

发明人： Holmes, Thomas J. ,  Cielaszyk, David

IPC分类号： G05D1/08

CPC分类号： G05D1/0883

摘要： Apparatus and a method is presented for controlling yaw and roll excursions in a spacecraft (20) having on-board components such as magnetic torquers (22,24), a roll thruster (32,34), momentum wheels (26,28,30), a wheel controller, an earth sensor, and a Digital Integrating Rate Assembly (DIRA). An observer module on the spacecraft receives inputs containing information comprising the unbiased roll error from the earth sensor, yaw momentum measured from the wheel speeds, and commanded yaw and pitch momentum output from the wheel controller, and produces therefrom output signals indicative of yaw estimate, yaw momentum estimate and torque disturbances estimate. A controller module on the spacecraft receives the output signals and combines them with inputs containing information comprising minimum yaw error and roll thrust yaw controller gain and minimum yaw error and roll thrust yaw momentum controller gain, and produces therefrom a signal for commanding the operation of the magnetic torquers to change roll momentum when within the dead band of the signal and, alternatively, for commanding the operation of both the magnetic torquers (22,24) and the roll thruster (32,34) to change roll momentum when the threshold of the dead band is exceeded. By so doing, the yaw attitude and yaw excursions are controlled.

公开(公告)号：EP1114774A2

公开(公告)日：2001-07-11

申请号：EP00311287.7

申请日：2000-12-15

申请人： Space Systems/Loral, Inc.

发明人： Tilley, Scott W. ,  Holmes, Thomas J. ,  Reckdahl, Keith J.

IPC分类号： B64G1/28

CPC分类号： B64G1/285 ,  B64G1/283 ,  B64G1/288 ,  B64G1/32 ,  B64G1/36 ,  B64G1/363 ,  B64G1/365 ,  G05D1/0883

摘要： An onboard attitude control system is constructed to utilize a four reaction wheel system (10-13) having a reference axis, wherein at least three of the reaction wheel spin axes are oriented obliquely to the reference axis. Current attitude is estimated based on uploaded orbital data, onboard sensed earth and sun position data, and attitude data sensed by a three axes gyroscope system (9). Current attitude is compared to mission attitude to calculate an error which is transformed to a trihedral axes adjustment command to actuate the reaction wheel system.

摘要翻译： 构造车载姿态控制系统以利用具有参考轴线的四个反作用轮系统（10-13），其中至少三个反作用轮旋转轴线相对于参考轴线倾斜定向。 目前的态度是根据上传的轨道数据，车载感测地面和太阳位置数据以及由三轴陀螺仪系统（9）感测到的姿态数据来估计的。 将当前姿态与任务姿态进行比较，以计算转换为三角轴调整命令以致动反作用轮系统的误差。

公开(公告)号：EP0892328B1

公开(公告)日：2002-12-04

申请号：EP98305731.6

申请日：1998-07-17

申请人： Space Systems/Loral, Inc.

发明人： Holmes, Thomas J.

IPC分类号： G05D1/08 ,  B64G1/26

CPC分类号： G05D1/0883 ,  B64G1/24 ,  B64G1/26 ,  B64G1/288 ,  B64G1/365 ,  B64G2001/245

公开(公告)号：EP1114774A3

公开(公告)日：2002-07-31

申请号：EP00311287.7

申请日：2000-12-15

申请人： Space Systems/Loral, Inc.

发明人： Tilley, Scott W. ,  Holmes, Thomas J. ,  Reckdahl, Keith J.

IPC分类号： B64G1/28

CPC分类号： B64G1/285 ,  B64G1/283 ,  B64G1/288 ,  B64G1/32 ,  B64G1/36 ,  B64G1/363 ,  B64G1/365 ,  G05D1/0883

摘要： An onboard attitude control system is constructed to utilize a four reaction wheel system (10-13) having a reference axis, wherein at least three of the reaction wheel spin axes are oriented obliquely to the reference axis. Current attitude is estimated based on uploaded orbital data, onboard sensed earth and sun position data, and attitude data sensed by a three axes gyroscope system (9). Current attitude is compared to mission attitude to calculate an error which is transformed to a trihedral axes adjustment command to actuate the reaction wheel system.

公开(公告)号：EP0892328A1

公开(公告)日：1999-01-20

申请号：EP98305731.6

申请日：1998-07-17

申请人： Space Systems/Loral, Inc.

发明人： Holmes, Thomas J.

IPC分类号： G05D1/08 ,  B64G1/26

CPC分类号： G05D1/0883 ,  B64G1/24 ,  B64G1/26 ,  B64G1/288 ,  B64G1/365 ,  B64G2001/245

摘要： A system and method is described for maintaining the attitude of a space craft to compensate for external disturbances. An on board computer (1) generates a thruster on time signal derived from a comparison of estimated adjusted attitude based substantially on rigid body assumptions which to do not take into consideration the flexing reactions of on board flexible components.

摘要翻译： 描述了一种用于维持航天器的姿态以补偿外部干扰的系统和方法。 车载计算机（1）基于实际上基于刚性身体假设的估计调节姿态的比较而产生推进器的时间信号，其不考虑船上柔性部件的弯曲反应。