发明名称 |
Attitude control system for three-axis stabilized satellite in near-equatorial orbit |
摘要 |
A roll/yaw attitude control system for a three-axis stabilized satellite in an at least approximately Equatorial orbit embodies a processor circuit connected between a roll, yaw and pitch attitude sensing device including a terrestrial sensor and a stellar sensor adapted to detect the Pole Star and an actuator device having a kinetic moment system substantially oriented along the pitch axis and a magnetic dipole generator system disposed at least approximately in a roll/yaw plane. The processor circuit embodies a short-term roll/yaw control loop adapted to estimate the roll and yaw attitude angles and angular speeds and to determine set point signals for some elements of the actuator device and a long-term roll/yaw control loop adapted to estimate roll/yaw attitude angles and external disturbances and to determine a dipole signal to be applied to the magnetic dipole generator system or to backup actuators.
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申请公布号 |
US5259577(A) |
申请公布日期 |
1993.11.09 |
申请号 |
US19910806607 |
申请日期 |
1991.12.12 |
申请人 |
AEROSPATIALE SOCIETE NATIONALE INDUSTRIELLE |
发明人 |
ACHKAR, ISSAM-MAURICE;GUILLERMIN, PIERRE |
分类号 |
B64G1/28;B64G1/24;B64G1/32;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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