| 发明名称 |
ESCAPING SINGULARITIES IN A SATELLITE ATTITUDE CONTROL |
| 摘要 |
Control moment gyros in an array are rotated to reorient a satellite by an attitude signal. If the signal causes a gyro to have position that will produce a singularity in attitude control, a disturbance is introduced into the signal to avoid the singularity. |
| 申请公布号 |
WO9950144(A2) |
申请公布日期 |
1999.10.07 |
| 申请号 |
WO1999US05598 |
申请日期 |
1999.03.16 |
| 申请人 |
HONEYWELL INC. |
发明人 |
HEIBERG, CHRISTOPHER, J.;BAILEY, DAVID, A. |
| 分类号 |
B64G1/28;B64G1/36;G05D1/08 |
主分类号 |
B64G1/28 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
|
| 地址 |
|
