发明名称 |
Gyroless control system for zero-momentum three-axis stabilized spacecraft |
摘要 |
A method for maintaining three axis control of a geosynchronous spacecraft without body rate measurements using reaction wheel assemblies. Earth sensor assembly angle measurements are utilized for high-bandwidth roll and pitch control. A positive pitch momentum bias is stored in the reaction wheel assemblies. A gyroscopic feedforward torque is applied to rotate reaction wheel assembly momentum in a yaw/roll plane of the spacecraft at orbit rate. A dynamic mode that couples yaw and roll axes and that results from applying the gyroscopic feedforward torque and the high-bandwidth roll control is damped based on earth sensor assembly roll measurements.
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申请公布号 |
US6600976(B1) |
申请公布日期 |
2003.07.29 |
申请号 |
US20020108626 |
申请日期 |
2002.03.29 |
申请人 |
LOCKHEED MARTIN CORPORATION |
发明人 |
GOODZEIT NEIL EVAN;LI XIPU;RATAN SANTOSH;WEIGL HARALD |
分类号 |
B64G1/28;B64G1/36;G05D1/08;(IPC1-7):B64G1/24 |
主分类号 |
B64G1/28 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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