| 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.
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| 申请公布号 |
US6047927(A) |
申请公布日期 |
2000.04.11 |
| 申请号 |
US19980039640 |
申请日期 |
1998.03.16 |
| 申请人 |
HONEYWELL INC. |
发明人 |
HEIBERG, CHRISTOPHER J.;BAILEY, DAVID A. |
| 分类号 |
B64G1/28;B64G1/36;G05D1/08;(IPC1-7):B64G1/28 |
主分类号 |
B64G1/28 |
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