Attitude determination and alignment using electro-optical sensors and global navigation satellites
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United States of America Patent
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Oct 8, 2002
Grant Date -
Jan 10, 2002
app pub date -
Mar 12, 2001
filing date -
Mar 10, 2000
priority date (Note) -
Expired
status (Latency Note)
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Abstract
An attitude determination and alignment method and system use electro-optical sensors and global navigation satellites to determine attitude knowledge for a spacecraft, satellite, or a high-altitude aircraft. An on-board inertial navigation system uses global navigation satellite system equipment and an attitude determination system uses an electro-optical sensor. The electro-optical sensor view the navigation satellites as surrogate stellar reference sources. The electro-optical sensor replaces the function of a star sensor or tracker and associated processing required for an onboard attitude determination system. Navigation and timing information generated by the GPS/GNSS-INS is used to perform required attitude determination system functions.
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