发明名称 |
Spacecraft gyro calibration system |
摘要 |
A method of calibrating a gyro ( 42 ) of a spacecraft ( 14 ) may include determining a yaw attitude residual of the spacecraft. Roll gyro bias residual is determined in response to the yaw attitude residual. The gyro ( 42 ) is calibrated in response to the roll gyro bias residual. A method of calibrating a gyro ( 42 ) of a spacecraft ( 14 ) may alternatively include disabling gyro calibration, gain scheduling, or resetting attitude and gyro bias covariance, for selective axes, for a yaw transient period. The gyro ( 42 ) is calibrated in a nominal fashion after completion of the yaw transient period.
|
申请公布号 |
US2005108884(A1) |
申请公布日期 |
2005.05.26 |
申请号 |
US20030723782 |
申请日期 |
2003.11.26 |
申请人 |
WANG HANGCHING G.;LI RONGSHENG K. |
发明人 |
WANG HANGCHING G.;LI RONGSHENG K. |
分类号 |
G01C19/00;(IPC1-7):G01C19/00 |
主分类号 |
G01C19/00 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|